CN107532611B - Compressor drum, compressor and gas turbine - Google Patents

Abstract

It is formed on armature spindle (21): the gas of gas compression flow path (19) being made to flow into the inlet fluid path (34d) of the lateral compartments (24) of downstream-side chamber group (22d)；The radial flow path (35) for being connected to the lateral compartments (24) of downstream-side chamber group (22d) with axial connecting chamber (25)；The axial flow path (37) for being connected to the axial connecting chamber (25) of downstream-side chamber group (22d) with the axial connecting chamber (25) of upstream side cavity group (22u)；The radial flow path (35) for being connected to the axial connecting chamber (25) of upstream side cavity group (22u) with lateral compartments (24)；And the outlet flow passage (34u) for flowing out the gas in the lateral compartments (24) of upstream side cavity group (22u) to gas compression flow path (19).

Description

Compressor rotor, compressor and gas turbine

Technical Field

The present invention relates to a compressor rotor, a compressor, and a gas turbine that rotate about an axis line in a compressor housing.

This application claims priority based on Japanese patent application No. 2015-090289, which was sun to this application on 27/4/2015, and this content is incorporated herein by reference.

Background

The compressor includes a casing and a rotor that rotates about an axis in the casing. The rotor of the axial flow compressor has: a rotor shaft extending in an axial direction with an axis as a center; and a plurality of rotor blade cascades fixed to the outer periphery of the rotor shaft and arranged in parallel in the axial direction.

As a rotor of the axial compressor as described above, there is a rotor disclosed in the following patent document 1. In the rotor, a plurality of cavities (or chambers) are formed in order to reduce the weight of the rotor. The first and second chambers of the plurality of chambers are positioned in the same radial direction and are axially juxtaposed. The second chamber is located on an axially upstream side with respect to the first chamber. Further, a third chamber of the plurality of chambers is formed at a position between the first chamber and the second chamber in the axial direction and at a position radially inward of the first chamber and the second chamber. The first chamber and the second chamber are both communicated with an air compression flow path formed by an annular space between the outer peripheral side of the rotor shaft and the inner peripheral side of the housing. The third chamber is in communication with the first chamber and also in communication with the second chamber.

A part of the air in the air compression flow path flows into the first chamber located on the downstream side of the second chamber. The air flows from the first chamber into the third chamber, and then returns to the air compression flow path through the second chamber.

Prior art documents

Patent document

Patent document 1: japanese patent laid-open publication No. 2013-204593

Disclosure of Invention

Problems to be solved by the invention

In the technique disclosed in patent document 1, a part of the air in the air compression flow path is returned to the air compression flow path via the chambers, thereby improving the thermal responsiveness of the rotor shaft with respect to a temperature change of the air flowing through the air compression flow path.

An object of the present invention is to provide a compressor rotor capable of further improving thermal responsiveness of a rotor shaft to a temperature change of air flowing through an air compression flow path, a compressor provided with the compressor rotor, and a gas turbine provided with the compressor.

Solution scheme

A compressor rotor according to a first aspect of the present invention for achieving the above object is a compressor rotor that rotates about an axis in a compressor housing, and includes: a rotor shaft extending in an axial direction around the axis; and a plurality of rotor blade cascades fixed to the outer periphery of the rotor shaft and arranged in parallel in the axial direction. In the rotor shaft, a plurality of groups of chambers are formed at respective positions in the axial direction between the plurality of rotor blade rows, and each group of chambers is formed by a plurality of chambers that are annular around the axis and are separated from each other in a radial direction with respect to the axis. The rotor shaft is disposed on an outer peripheral side of the rotor shaft, and a side of the gas compression flow path on which a pressure of the gas is low is an upstream side in the axial direction. Among the plurality of chambers constituting the chamber group, a chamber located radially outermost is an outer chamber, and any one of the chambers located radially inward of the outer chamber is an axially communicating chamber. At least one chamber group on the upstream side among the at least two chamber groups is an upstream side chamber group, and the remaining chamber group on the downstream side with respect to the upstream side chamber group is a downstream side chamber group. Further formed on the rotor shaft are: an inlet flow path that causes the gas in the gas compression flow path to flow into the outer chambers of the downstream side chamber group; a radial flow path that extends in a direction including the radial direction, and that causes two chambers adjacent in the radial direction, from among a plurality of chambers from the outer chamber to the axial communication chamber, to communicate with each other so that a gas that has flowed into the outer chamber of the downstream-side chamber group reaches the axial communication chamber of the downstream-side chamber group; an axial flow path that extends in a direction including the axial direction and that communicates the axial communication chambers of the downstream side chamber group with the axial communication chambers of the upstream side chamber group; a radial flow path that extends in a direction including the radial direction, and that causes two chambers adjacent in the radial direction, from among a plurality of chambers from the axial direction communication chamber to the outer chamber, to communicate with each other so that a gas in the axial direction communication chamber of the upstream side chamber group reaches the outer chamber of the upstream side chamber group; and an outlet passage that flows out the gas in the outer chamber of the upstream chamber group into the gas compression passage. A radially outer edge of the axial flow path, which is an inlet opening corresponding to an opening of the axial communication chamber of the downstream side chamber group, is located radially inward of a radially outer inner peripheral surface of an inner peripheral surface defining the annular axial communication chamber, and a radially outer edge of the axial flow path, which is an outlet opening corresponding to an opening of the axial communication chamber of the upstream side chamber group, is located radially inward of a radially outer inner peripheral surface of an inner peripheral surface defining the annular axial communication chamber.

In this compressor rotor, a part of the gas in the gas compression flow path flows into the outer chamber of the downstream chamber group through the inlet flow path using the pressure difference in the axial direction in the gas compression flow path as a driving force. The gas flowing into the outer chamber flows into the axial communication chamber of the downstream side chamber group through the radial flow path and, as the case may be, further through one or more chambers. The gas flowing into the axial communication chamber of the downstream side chamber group flows into the axial communication chamber of the upstream side chamber group through the axial flow path. The gas flowing into the axially communicating chamber of the upstream side chamber group flows into the outer side chamber of the upstream side chamber group through the radial flow path and further through one or more chambers as the case may be. The gas flowing into the outer chamber of the upstream chamber group is returned to the gas compression flow path through the outlet flow path.

Therefore, in the compressor rotor, the pressure difference in the axial direction in the air compression flow passage is used as the driving force, and the inside of the outer chamber of the downstream side chamber group, the chamber between the outer chamber of the downstream side chamber group and the axial direction communication chamber, and the inside of the outer chamber of the upstream side chamber group, the chamber between the outer chamber of the upstream side chamber group and the axial direction communication chamber can be effectively ventilated by a part of the gas in the gas compression flow passage. In the compressor rotor, the gas in the gas compression flow passage can be effectively ventilated even between the position where the radial outer edge of the axial communication chamber of the downstream chamber group is radially open and the position where the axial flow passage of the axial communication chamber of the upstream chamber group is radially open and the position where the radial outer edge of the axial communication chamber of the downstream chamber group is radially open. In the compressor rotor, the heat conductivity of the wall surface defining the chamber can be increased by utilizing the difference in the peripheral velocity between the air flowing in the chamber and the chamber.

Therefore, in the compressor rotor, the thermal responsiveness of the compressor rotor with respect to a temperature change of the gas flowing through the gas compression flow path can be improved.

A compressor rotor according to a second aspect of the present invention for achieving the above object is the compressor rotor according to the first aspect, wherein a radially outer edge of the inlet opening in the axial flow passage is located radially inward of a radially central position of the axial communication chamber of the downstream side chamber group, and a radially outer edge of the outlet opening in the axial flow passage is located radially inward of a radially central position of the axial communication chamber of the upstream side chamber group.

In this compressor rotor, the axial communication chambers of the downstream side chamber group and the axial communication chambers of the upstream side chamber group can be ventilated over a wide range by the gas in the gas compression flow path. In the compressor rotor, the heat conductivity of the wall surface defining the chamber can be increased by the difference in the peripheral speed between the air flowing in the chambers and the chambers. Therefore, in the compressor rotor, the thermal responsiveness of the compressor rotor with respect to a temperature change of the gas flowing through the gas compression flow path can be further improved.

A compressor rotor according to a third aspect of the invention for achieving the above object is the compressor rotor according to the first or second aspect, wherein the rotor shaft is formed with a plurality of axial flow passages separated from each other in a circumferential direction with respect to the axis.

In this compressor rotor, the circumferential speed of the gas flowing through the axial flow passage is limited by the circumferential speed of the rotor shaft, and is substantially the same as the circumferential speed of the rotor shaft. On the other hand, since each of the axial direction communication chambers communicating with the axial direction flow passage is formed in a ring shape with the axis as the center, the gas flowing in the axial direction communication chamber is not substantially restricted by the circumferential speed of the rotor shaft. Therefore, a difference in circumferential velocity occurs between the gas flowing through each of the axially communicating chambers and the circumferential velocity of the rotor shaft. In particular, the radial outer side in the axially communicating chamber of the upstream chamber group has a larger circumferential speed difference with respect to the circumferential speed of the rotor shaft than the radial inner side. Therefore, the thermal conductivity between the surface of the rotor shaft constituent member defining the chamber and the air can be improved.

Therefore, in the compressor rotor, the thermal responsiveness of the compressor rotor with respect to a temperature change of the gas flowing through the gas compression flow path can be further improved.

A compressor rotor according to a fourth aspect of the present invention for achieving the above object is the compressor rotor according to any one of the first to third aspects, wherein the compressor rotor includes at least one inlet side portion of an inlet side portion of the radial flow passage and an inlet side portion of the axial flow passage, the inlet side portion of the radial flow passage includes the inlet opening in which an inlet opening that is a radially inner opening in the radial flow passage of the upstream chamber group is inclined toward a rotation direction side of the rotor shaft, and the inlet side portion of the axial flow passage includes the inlet opening in which the inlet opening in the axial flow passage is inclined toward a side opposite to the rotation direction side of the rotor shaft.

In the compressor rotor according to any one of the above aspects, at least one of an inlet side portion of the radial flow passage including an inlet opening that is an opening on a radially outer side of the radial flow passage that connects the outer chamber of the downstream chamber group and the chamber adjacent to the outer chamber in the radial direction, and an inlet side portion of the radial flow passage including an inlet opening that is an opening on a radially inner side of the radial flow passage of the upstream chamber group may be inclined toward a rotation direction side of the rotor shaft.

In any of the above compressor rotors, an inlet side portion of the axial flow passage including the inlet opening in the axial flow passage may be inclined toward a side opposite to a rotation direction side of the rotor shaft.

A compressor rotor according to a fifth aspect of the invention for achieving the above object is the compressor rotor according to any one of the first to fourth aspects, wherein the downstream side chamber group has three or more chambers, an inlet side portion of the radial flow path including an inlet opening that is an opening on a radially outer side of the radial flow path is inclined so as to face a side opposite to a rotation direction side of the rotor shaft, and the radial flow path causes two or more chambers other than the outer chamber among the three or more chambers to communicate with each other.

In this compressor rotor, even if there is a difference in peripheral speed between the gas and the flow path, the gas is received by the inlet opening of the flow path, and therefore the gas can be smoothly flowed into the flow path.

A compressor rotor according to a sixth aspect of the present invention for achieving the above object is the compressor rotor according to any one of the first to fifth aspects, wherein any one of an outlet side portion of the radial flow passage including an outlet opening that is an opening on a radially inner side of the radial flow passage of the downstream side chamber group, an outlet side portion of the radial flow passage including an outlet opening that is an opening on a radially outer side of the radial flow passage of the upstream side chamber group, and an outlet side portion of the axial flow passage including the outlet opening in the axial flow passage is inclined toward a side in a rotation direction of the rotor shaft or a side opposite to the rotation direction of the rotor shaft.

A compressor rotor according to a seventh aspect of the present invention for achieving the above object is the compressor rotor according to any one of the first to sixth aspects, wherein an inlet side portion of the flow path including the inlet opening has a flow path inner diameter that gradually decreases from the inlet opening toward an outlet opening side on a side opposite to the inlet opening of the flow path.

A compressor rotor according to an eighth aspect of the present invention for achieving the above object is the compressor rotor according to any one of the first to seventh aspects, wherein the rotor shaft includes: a plurality of rotor disks stacked on each other in the axial direction; and torque pins that extend in the radial direction and engage with the rotor disks adjacent in the axial direction, respectively, to restrict relative rotation between the adjacent rotor disks, the torque pins being disposed at two positions: that is, the positions of chambers adjacent in the radial direction among the plurality of chambers constituting the downstream side chamber group; and a through hole penetrating in the radial direction is formed in the torque pin, and the through hole forms the radial flow passage.

In this compressor rotor, if the through holes are formed in the torque pins, it is not necessary to form radial flow paths in the rotor disk. Therefore, in the compressor rotor, the number of machining steps for the rotor disk can be suppressed from increasing.

A compressor rotor according to a ninth aspect of the present invention for achieving the above object is the compressor rotor according to any one of the first to eighth aspects, wherein the rotor shaft includes: a plurality of rotor disks stacked on each other in the axial direction; and a spindle bolt extending in the axial direction and penetrating the plurality of rotor disks, the axial communication chamber of the downstream side chamber group, and the axial communication chamber of the upstream side chamber group, a bolt through hole having a clearance extending in the axial direction between the bolt through hole and the spindle bolt, the bolt through hole being formed in a rotor disk existing between the axial communication chamber of the downstream side chamber group and the axial communication chamber of the upstream side chamber group and through which the spindle bolt penetrates, the clearance of the bolt through hole forming the axial flow path.

A compressor rotor according to a tenth aspect of the present invention for achieving the above object is the compressor rotor according to the ninth aspect, wherein the gap in the bolt through hole, which forms the axial flow passage, is located radially inward of the spindle bolt.

A compressor rotor according to an eleventh aspect of the present invention for achieving the above object is the compressor rotor according to any one of the first to tenth aspects, wherein a radially innermost chamber of the plurality of chambers constituting the chamber group is the axially communicating chamber.

In the compressor rotor, all of the plurality of chambers constituting the chamber group can be efficiently ventilated by the gas in the gas compression flow passage. Therefore, in the compressor rotor, the thermal responsiveness of the compressor rotor with respect to a temperature change of the gas flowing through the gas compression flow path can be further improved.

A compressor rotor according to a twelfth aspect of the present invention for achieving the above object is the compressor rotor according to any one of the first to eleventh aspects, wherein the upstream chamber group is composed of the upstream-side chambers in the two axially adjacent chamber groups, and the downstream-side chamber group is composed of the downstream-side chambers.

A compressor according to a thirteenth aspect of the present invention for achieving the above object includes the compressor rotor according to any one of the first to twelfth aspects and the compressor housing.

A gas turbine according to a fourteenth aspect of the present invention for achieving the above object includes the compressor according to the thirteenth aspect, and a combustor that combusts fuel in air compressed by the compressor to generate combustion gas; and a turbine driven by the combustion gases.

Effects of the invention

According to one aspect of the present invention, the thermal responsiveness of the rotor shaft with respect to a temperature change of air flowing through the air compression flow passage can be further improved.

Drawings

Fig. 1 is a sectional side view of a main part of a gas turbine in an embodiment of the present invention.

Fig. 2 is a sectional view of a main part of a compressor in the first embodiment of the present invention.

Fig. 3 shows a rotor disk in a first embodiment of the present invention, fig. 3 (a) is a sectional view of the rotor disk, and fig. 3 (B) is a view from B in fig. 3 (a).

Fig. 4 is a sectional view of a main part around a blade and a vane of a compressor according to a first embodiment of the present invention.

Fig. 5 is a perspective view of a torque pin in the first embodiment of the present invention.

Fig. 6 is an explanatory diagram illustrating the flow of gas in the compressor in the first embodiment of the present invention.

Fig. 7 is a graph showing changes in the circumferential velocity of the gas in the rotor shaft in the first embodiment of the present invention.

Fig. 8 is a graph showing changes in the circumferential velocity of the gas in the rotor shaft in the comparative example to the first embodiment of the present invention.

Fig. 9 is a cross-sectional view of a main part of a rotor shaft in a comparative example to the first embodiment of the present invention.

Fig. 10 is a sectional view of a main part of a compressor in a second embodiment of the present invention.

Fig. 11 shows a rotor disk in a second embodiment of the present invention, fig. 11 (a) is a sectional view of the rotor disk, and fig. 11 (B) is a view from B in fig. 11 (a).

Fig. 12 is an explanatory diagram illustrating a flow of gas in the compressor in the second embodiment of the present invention.

Fig. 13 is a graph showing changes in the circumferential velocity of the gas in the rotor shaft in the second embodiment of the present invention.

Fig. 14 is a view corresponding to the XIV view in fig. 11, and is a view of a rotor disk in the first modification of the second embodiment of the present invention.

Fig. 15 is a view corresponding to the XV view in fig. 11, and is a view of a rotor disk in the first modification of the second embodiment of the present invention.

Fig. 16 is a detailed schematic view around the position P2 in fig. 14.

Fig. 17 is a detailed schematic view around the position P3 in fig. 14.

Fig. 18 is a detailed schematic view around the position P4 in fig. 14.

Fig. 19 is a detailed schematic view around the position P5 in fig. 15.

Fig. 20 is a detailed schematic view around the position P6 in fig. 15.

Fig. 21 is a perspective view of a torque pin of the downstream side chamber group in the first modification of the second embodiment of the present invention.

Fig. 22 is a perspective view of a torque pin of the upstream side chamber group in the first modification of the second embodiment of the present invention.

Fig. 23 is a detailed schematic view of the vicinity of a position P7 or P8 in fig. 14, according to a second modification of the second embodiment of the present invention.

Fig. 24 is another example of the second modification of the second embodiment of the present invention, and is a detailed schematic view of the vicinity of the position P7 or P8 in fig. 14.

Fig. 25 is a detailed schematic view of the vicinity of a position P9 in fig. 15, which is a second modification of the second embodiment of the present invention.

Fig. 26 is another example of the second modification of the second embodiment of the present invention, and is a detailed schematic view of the vicinity of position P9 in fig. 15.

Fig. 27 is a detailed schematic view of the vicinity of a position P10 in fig. 15, which is a second modification of the second embodiment of the present invention.

Fig. 28 is another example of the second modification of the second embodiment of the present invention, and is a detailed schematic view of the vicinity of position P10 in fig. 15.

Fig. 29 is a detailed schematic view of the vicinity of a position P11 in fig. 15, which is a second modification of the second embodiment of the present invention.

Fig. 30 is a cross-sectional view of a radial flow passage or an axial flow passage according to a third modification of the second embodiment of the present invention.

Fig. 31 is a cross-sectional view of a radial flow passage or an axial flow passage in another example of the third modification of the second embodiment of the present invention.

Fig. 32 is an explanatory diagram illustrating a flow of gas in the compressor in another modification of the first embodiment of the present invention.

Detailed Description

Hereinafter, various embodiments of the present invention will be described in detail with reference to the drawings.

[ gas turbine embodiment ]

An embodiment of a gas turbine will be described with reference to fig. 1.

As shown in fig. 1, the gas turbine of the present embodiment includes a compressor 1, a combustor 2, and a turbine 3. The compressor 1 compresses external air to generate compressed air. The combustor 2 mixes fuel from a fuel supply source with compressed air and combusts the fuel and the compressed air to generate combustion gas. The turbine 3 is driven by the combustion gas.

The compressor 1 includes: a compressor rotor 20 that rotates about an axis Ar; and a cylindrical compressor housing 10 covering the compressor rotor 20. In the following, the direction in which the axis Ar extends is referred to as the axial direction Da. One side in the axial direction Da is an upstream side, and the other side in the axial direction is a downstream side. Only the radial direction with respect to the axis Ar is set as the radial direction Dr. Further, a side distant from the axis Ar in the radial direction Dr is a radially outer side, and a side close to the axis Ar in the radial direction Dr is a radially inner side. The upstream side of the compressor housing 10 is formed with an opening. This opening serves as an intake port 11i through which the compressor 1 takes in air from the outside.

The turbine 3 is disposed downstream of the compressor 1. The turbine 3 includes: a turbine rotor 4 that rotates about an axis Ar; and a cylindrical turbine housing 5 covering the turbine rotor 4. The compressor rotor 20 and the turbine rotor 4 rotate about the same axis Ar, and are connected to each other to form a gas turbine rotor 8. The compressor casing 10 and the turbine casing 5 are connected to each other to form a gas turbine casing 9. The combustor 2 is fixed to the gas turbine casing 9.

[ first embodiment of compressor ]

A first embodiment of the compressor will be described with reference to fig. 2 to 9.

The compressor of the present embodiment is the compressor 1 of the gas turbine described above. Therefore, the compressor 1 of the present embodiment includes a compressor rotor 20 that rotates about the axis Ar, and a cylindrical compressor housing 10 that covers the compressor rotor 20.

As shown in fig. 2, the compressor 1 is an axial compressor. The compressor rotor 20 has a rotor shaft 21 and a plurality of moving blade cascades 81. The rotor shaft 21 extends in the axial direction Da around the axis Ar. The plurality of rotor blade cascades 81 are fixed to the outer periphery of the rotor shaft 21 and arranged in parallel in the axial direction Da. A stationary blade cascade 11 is fixed to a position on the inner peripheral side of the compressor casing 10 and downstream of each of the rotor blade cascades 81.

One stationary blade cascade 11 has a plurality of stationary blades 12. The plurality of vanes 12 are arranged in the circumferential direction Dc about the axis Ar to form one vane cascade 11. In addition, one bucket cascade 81 has a plurality of buckets 82. The plurality of rotor blades 82 are arranged in the circumferential direction Dc about the axis Ar to form one rotor blade cascade 81.

As shown in fig. 4, the vane 12 includes a blade body 13 extending in the radial direction Dr, an outer shroud 14 provided outside the blade body 13 in the radial direction Dr, and an inner shroud 15 provided inside the blade body 13 in the radial direction Dr. The outer shroud 14 is attached to the inner peripheral side of the compressor housing 10. A seal ring 16 is provided radially Dr inside the inner shroud 15. The rotor blade 82 includes a blade body 83 extending in the radial direction Dr, a platform 84 provided on the inner side of the blade body 83 in the radial direction Dr, and a blade root 85 provided on the inner side of the platform 84 in the radial direction Dr. The blade root 85 is embedded in the rotor shaft 21.

In the compressor 1, the air compression flow path 19 through which air in a compression process passes is annular around the axis Ar. The outer peripheral side of the air compression flow path 19 is defined by the compressor casing 10 and the outer shroud 14 of the stator vane 12. The inner periphery of the air compression flow path 19 is defined by the platform 84 of the blade 82 and the inner shroud 15 of the vane 12. The air is compressed in the air compression flow passage 19 by the rotation of the compressor rotor 20 and flows from the upstream side to the downstream side.

As shown in fig. 2, the rotor shaft 21 has a plurality of cavities 23 formed at respective positions in the axial direction Da of the plurality of blade cascades 81, in other words, at respective positions in the axial direction Da of the plurality of stationary blade cascades 11. The plurality of chambers 23 are annular around the axis Ar and are separated from each other in the radial direction Dr. The plurality of chambers 23 formed at the positions in the axial direction Da between the two moving blade cascades 81 adjacent in the axial direction Da constitute one chamber group 22. Therefore, the plurality of chamber groups 22 are formed in parallel in the axial direction Da on the rotor shaft 21.

One chamber group 22 is constituted by three chambers of an outer chamber 24, an intermediate chamber 25, and an inner chamber 26. The outer chamber 24 is formed in the rotor shaft 21 at a position most outside in the radial direction Dr among the plurality of chambers. The intermediate chamber 25 is formed radially inside Dr of the outer chamber 24. The inner chamber 26 is formed in the rotor shaft 21 at a position most inward in the radial direction Dr among the plurality of chambers.

The rotor shaft 21 is further provided with a radial outer passage 34 that communicates the outer chamber 24 with the air compression passage 19, and a plurality of radial intermediate passages 35 that communicate the outer chamber 24 with the intermediate chamber 25. The radially outer flow path 34 is a flow path that extends in an annular shape with the axis Ar as the center. On the other hand, the plurality of radial intermediate flow passages 35 are separated from each other in the circumferential direction Dc.

The rotor shaft 21 has a plurality of rotor disks 41, a main shaft bolt 51, and a torque pin 55. The plurality of rotor disks 41 are stacked on each other in the axial direction Da. The spindle bolts 51 extend in the axial direction Da through the plurality of rotor disks 41 and the plurality of intermediate cavities 25. The torque pin 55 restricts relative rotation of the adjacent rotor disks 41.

A rotor blade cascade 81 is mounted on one rotor disk 41. Thus, a rotor disk 41 is present for each of the plurality of bucket cascades 81.

As shown in fig. 3, the plurality of cavities 23 constituting one cavity group 22, the radial outer passage 34 communicating the outer cavity 24 of the cavity group 22 with the air compression passage 19, and the radial intermediate passage 35 communicating the outer cavity 24 of the cavity group 22 with the intermediate cavity 25 are formed between two rotor disks 41 adjacent in the axial direction Da. Fig. 3 (a) is a sectional view of the rotor disk 41, and fig. 3 (B) is a view in the direction B of fig. 3 (a).

An upstream first concave portion 43u, an upstream second concave portion 45u, and an upstream third concave portion 47u are formed on the upstream side of one rotor disc 41. The upstream-side first concave portion 43u is recessed toward the downstream side to form the upstream-side outer cavity 24 of the rotor disc 41. The upstream second concave portion 45u is recessed toward the downstream side to form the intermediate cavity 25 on the upstream side of the rotor disk 41. The upstream third recessed portion 47u is recessed toward the downstream side to form the inside cavity 26 on the upstream side of the rotor disk 41. Therefore, an annular upstream-side first arm portion 42u is formed to protrude toward the upstream side in the axial direction Da relative to the bottom surface of the upstream-side first concave portion 43u on the radially Dr outer side of the upstream-side first concave portion 43 u. Further, between the upstream-side first recess 43u and the upstream-side second recess 45u, an annular upstream-side second arm portion 44u is formed which projects toward the upstream side in the axial direction Da relative to the bottom surface of the upstream-side first recess 43u and the bottom surface of the upstream-side second recess 45 u. Further, an annular upstream third arm 46u is formed between the upstream second concave portion 45u and the upstream third concave portion 47u so as to project toward the upstream side in the axial direction Da relative to the bottom surface of the upstream second concave portion 45u and the bottom surface of the upstream third concave portion 47 u.

The annular upstream second arm portion 44u has a plurality of upstream pin grooves 44up recessed toward the downstream side and communicating the upstream first recess 43u with the upstream second recess 45 u.

Further, a downstream side first concave portion 43d, a downstream side second concave portion 45d, and a downstream side third concave portion 47d are formed on the downstream side of one rotor disk 41. The downstream first concave portion 43d is recessed toward the upstream side to form the downstream outer cavity 24 of the rotor disk 41. The downstream second concave portion 45d is recessed toward the upstream side to form the intermediate cavity 25 on the downstream side of the rotor disk 41. The downstream third recessed portion 47d is recessed toward the upstream side to form the inner cavity 26 on the downstream side of the rotor disk 41. Therefore, an annular downstream first arm portion 42d that projects toward the downstream side in the axial direction Da relative to the bottom surface of the downstream first recess portion 43d is formed on the radially Dr outer side of the downstream first recess portion 43 d. Further, an annular downstream second arm portion 44d is formed between the downstream first concave portion 43d and the downstream second concave portion 45d so as to project toward the downstream side in the axial direction Da with respect to the bottom surface of the downstream first concave portion 43d and the bottom surface of the downstream second concave portion 45 d. Further, an annular downstream third arm 46d is formed between the downstream second recess 45d and the downstream third recess 47d so as to project toward the downstream side in the axial direction Da with respect to the bottom surface of the downstream second recess 45d and the bottom surface of the downstream third recess 47 d.

The annular downstream second arm portion 44d has a plurality of downstream pin grooves 44dp that are recessed toward the upstream side and communicate the downstream first concave portion 43d with the downstream second concave portion 45 d.

The outer cavity 24 is defined by the downstream side first concave portion 43d of the upstream side rotor disk 41 and the upstream side first concave portion 43u of the downstream side rotor disk 41 of the two adjacent rotor disks 41 in the axial direction Da. The middle cavity 25 is defined by the downstream side second concave portion 45d of the upstream side rotor disk 41 and the upstream side second concave portion of the downstream side rotor disk 41 of the two rotor disks 41 adjacent in the axial direction Da. The inner cavity 26 is defined by the downstream-side third concave portion 47d of the upstream-side rotor disk 41 and the upstream-side third concave portion 47u of the downstream-side rotor disk 41 of the two adjacent rotor disks 41 in the axial direction Da.

The downstream side first arm portion 42d of the upstream side rotor disk 41 of the two rotor disks 41 adjacent in the axial direction Da and the upstream side first arm portion 42u of the downstream side rotor disk 41 face each other and are separated in the axial direction Da. The radially outer flow path 34 is defined by the downstream side first arm portion 42d of the upstream side rotor disk 41 of the two rotor disks 41 adjacent in the axial direction Da and the upstream side first arm portion 42u of the downstream side rotor disk 41.

The plurality of downstream side pin grooves 44dp of the upstream side rotor disk 41 of the two rotor disks 41 adjacent in the axial direction Da and the plurality of upstream side pin grooves 44up of the downstream side rotor disk 41 face each other in the axial direction Da. The pin hole into which the torque pin 55 is fitted is defined by a downstream side pin groove 44dp and an upstream side pin groove 44 up. The pin hole into which the torque pin 55 is fitted is formed in a cylindrical shape corresponding to the shape of the cylindrical torque pin 55.

The rotor disk 41 is formed with a bolt through hole 48 through which the spindle bolt 51 passes from the bottom surface of the upstream second recessed portion 45u to the bottom surface of the downstream second recessed portion 45 d. Further, a rotor blade mounting portion 49 to which a blade root 85 (see fig. 4) of the rotor blade 82 is mounted is formed between the upstream side first arm portion 42u and the downstream side second arm portion 44d on the outer side in the radial direction Dr of the rotor disk 41.

As shown in fig. 5, a cylindrical torque pin 55 is formed with a through hole 56 penetrating from one end face to the other end face of the cylinder. The through hole 56 forms the radial intermediate flow passage 35.

As shown in fig. 2, the first chamber group 22 on the most downstream side of the rotor shaft 21 and the second chamber group 22 on the upstream side adjacent to the first chamber group 22 in the axial direction Da form a set. In this group, the first chamber group 22 becomes the downstream side chamber group 22d, and the second chamber group 22 becomes the upstream side chamber group 22 u. The third chamber group 22 on the upstream side adjacent to the second chamber group 22 in the axial direction Da and the fourth chamber group 22 on the upstream side adjacent to the third chamber group 22 in the axial direction Da are grouped. In this group, the third chamber group 22 becomes the downstream side chamber group 22d, and the fourth chamber group 22 becomes the upstream side chamber group 22 u. The fifth chamber group 22 on the upstream side adjacent to the fourth chamber group 22 in the axial direction Da and the sixth chamber group 22 on the upstream side adjacent to the fifth chamber group 22 in the axial direction Da are grouped. In this group, the fifth chamber group 22 becomes the downstream side chamber group 22d, and the sixth chamber group 22 becomes the upstream side chamber group 22 u.

The radially outer passage 34, which connects the outer chamber 24 of the downstream side chamber group 22d and the air compression passage 19, serves as an inlet passage 34d through which the air in the air compression passage 19 flows into the outer chamber 24. Further, the radially outer passage 34, which connects the outer chamber 24 of the upstream chamber group 22u and the air compression passage 19, serves as an outlet passage 34u through which the air in the outer chamber 24 flows out into the air compression passage 19.

An axial flow passage 37 is formed in the rotor disc 41 between the downstream side chamber group 22d and the upstream side chamber group 22u so as to communicate the intermediate chamber 25 of the downstream side chamber group 22d with the intermediate chamber 25 of the upstream side chamber group 22 u. As shown in fig. 3, a gap 48s extending in the axial direction Da is formed between the bolt through hole 48 of the rotor disk 41 and the surface on the inner side in the radial direction Dr of the spindle bolt 51 inserted therethrough. The gap 48s forms the axial flow passage 37. The opening of the axial flow passage 37 to the intermediate chamber 25 of the downstream chamber group 22d is an inlet opening 37 i. The opening of the axial flow passage 37 to the intermediate chamber 25 of the upstream chamber group 22u is an outlet opening 37 o. The radial Dr outer edge of the inlet opening 37i in the axial flow passage 37 is located radially inward of the radial Dr center position of the intermediate chamber 25 in the downstream chamber group 22 d. Similarly, the outer edge of the outlet opening 37o in the axial flow path 37 in the radial direction Dr is also located radially inward of the central position in the radial direction Dr of the intermediate chamber 25 of the upstream chamber group 22 u. The central position in the radial direction Dr of the intermediate chamber 25 indicates a position 1/2 that defines a height in the radial direction Dr from the radially inner peripheral surface to the radially outer peripheral surface in the inner peripheral surface of the annular intermediate chamber 25.

In this manner, in the present embodiment, the axial flow passage 37 is formed to communicate the intermediate chamber 25 of the downstream chamber group 22d with the intermediate chamber 25 of the upstream chamber group 22 u. Therefore, in the present embodiment, the intermediate chamber 25 of the downstream side chamber group 22d and the intermediate chamber 25 of the upstream side chamber group 22u both become axially communicating chambers. In the rotor disk 41, a plurality of bolt through holes 48 through which the spindle bolts 51 are inserted are formed in parallel in the circumferential direction Dc about the axis Ar. Therefore, the rotor disk 41 is also formed with a plurality of axial flow passages 37 arranged in parallel in the circumferential direction Dc about the axis Ar.

Next, the flow of air in the compressor housing 10 will be described with reference to fig. 6.

When the air supplied from the intake port 11i of the compressor housing 10 flows into the air compression flow path 19, the air is gradually compressed while flowing downstream in the air compression flow path 19. Therefore, the pressure in the air compression flow path 19 is high on the downstream side. Therefore, the pressure in the radially outer passage 34 of the downstream side chamber group 22d communicating with the downstream side air compression passage 19 with reference to the one rotor blade cascade 81 is higher than the pressure in the radially outer passage 34 of the upstream side chamber group 22u communicating with the upstream side air compression passage 19 with reference to the one rotor blade cascade 81. Therefore, the air in the air compression flow passage 19 flows into the radially outer flow passage 34 of the downstream chamber group 22 d. Therefore, the radially outer flow passage 34 functions as the inlet flow passage 34d as described above.

The air flowing into the inlet flow path 34d flows into the outer chamber 24 of the downstream chamber group 22 d. The air flows into the intermediate chamber 25 through the radial intermediate flow passage 35 formed in the torque pin 55. The air flowing into the intermediate chamber 25 flows into the intermediate chamber 25 of the upstream chamber group 22u through the axial flow path 37 formed by the gap 48s between the bolt through hole 48 of the rotor disk 41 and the spindle bolt 51. This air flows into the outer chamber 24 of the upstream chamber group 22u through the radial intermediate flow path 35 formed in the torque pin 55. The air that has flowed into the outer chamber 24 flows out to the air compression flow passage 19 from the radial outer flow passage 34 that connects the outer chamber 24 of the upstream chamber group 22u and the air compression flow passage 19. Therefore, the radially outer flow passage 34 functions as the outlet flow passage 34u as described above.

That is, in the present embodiment, a circulating flow is generated in which a part of the air in the air compression passage 19 passes through the downstream side chamber group 22d and the upstream side chamber group 22u from here and returns to the air compression passage 19, using a pressure difference in the axial direction Da in the air compression passage 19 as a driving force. The circulating flow promotes ventilation in each chamber in the rotor shaft 21.

However, as shown in fig. 4, a gap is formed between the radial outer end of the rotor blade 82 and the inner circumferential surface of the compressor casing 10 facing the radial outer end in the radial direction Dr. This clearance is generally called a tip clearance CC, and is preferably as small as possible from the viewpoint of compressor performance.

The dimension in the radial direction Dr of the compressor rotor 20, in particular the rotor shaft 21, is greater than the thickness dimension in the radial direction Dr of the compressor housing 10. Therefore, the heat capacity of the compressor rotor 20 is larger than that of the compressor housing 10, and the thermal responsiveness of the compressor rotor 20 with respect to the temperature change of the air flowing in the air compression flow path 19 is lower than that of the compressor housing 10. Therefore, when the temperature of the air flowing through the air compression flow path 19 changes, the tip clearance CC changes due to the difference in thermal responsiveness between the compressor rotor 20 and the compressor housing 10.

In the case where the variation of the tooth tip clearance CC is large, the steady-state clearance needs to be increased. The steady-state clearance is the tooth tip clearance CC when the gas turbine continues to operate in a steady state and both the compressor rotor 20 and the compressor casing 10 continue to reach the same temperature. When the steady-state clearance is large, the amount of air passing between the radially outer end of the rotor blade 82 and the inner circumferential surface of the compressor casing 10 increases during steady-state operation of the gas turbine. Therefore, when the steady clearance is large, not only the compressor performance during steady operation of the gas turbine but also the gas turbine performance becomes low.

In contrast, in the present embodiment, as described above, the air in the air compression flow path 19 flows through the rotor shaft 21, so that the thermal responsiveness of the compressor rotor 20 with respect to the temperature change of the air flowing through the air compression flow path 19 is improved, and the variation in the tip clearance CC is reduced. In the present embodiment, since the variation in the tooth tip clearance CC is reduced in this manner, the steady-state clearance can be reduced. Therefore, in the present embodiment, the compressor performance during steady-state operation of the gas turbine can be improved, and as a result, the gas turbine performance can be improved.

Next, the reason why the thermal responsiveness of the compressor rotor 20 is improved in the present embodiment will be described with reference to fig. 7 and 8. In fig. 7 and 8, the horizontal axis represents the circumferential velocity of air, and the vertical axis represents the distance from the axis Ar in the radial direction Dr. In fig. 7 and 8, the thick broken line indicates the circumferential speed of the rotor shaft 21, and the thin solid line indicates the circumferential speed of the air in the rotor shaft 21.

Fig. 7 shows a change in the circumferential velocity of air in the rotor shaft 21 in the present embodiment. As shown in fig. 7, the circumferential speed at a position on the axis Ar of the rotor shaft 21 is 0. Further, the rotor shaft 21 increases the circumferential speed in proportion to the distance from the axis Ar as it goes away from the axis Ar. Therefore, the maximum circumferential speed V is set at the outer circumferential surface of the rotor shaft 21.

As described with reference to fig. 6, the air in the air compression flow passage 19 flows into the outer chamber 24 of the downstream chamber group 22d through the inlet flow passage 34 d. The circumferential velocity V1 of the air immediately after flowing into the outer chamber 24 can be 0.5V, which is substantially half of the circumferential velocity V in the outer circumferential surface of the rotor shaft 21. Here, although the peripheral speed V1 of the air immediately after flowing into the outer chamber 24 is set to 0.5V, this is merely an example, and the peripheral speed V1 can be changed by gap adjustment or the like. The air flowing into the outer chamber 24 flows in the outer chamber 24 in the circumferential direction Dc and radially Dr inward relative to the outer chamber 24. The circumferential velocity of the air increases in inverse proportion to the distance from the axis Ar according to the law of preservation of the amount of angular motion. Therefore, as the air flows radially inside Dr in the outer chamber 24, the peripheral speed of the air increases. When the air reaches the radially Dr inner end of the outer chamber 24, the circumferential velocity of the air becomes v 2. The peripheral speed v2 is higher than the peripheral speed v1 of the air immediately after flowing into the outer chamber 24. The air flows into any one of the plurality of radial intermediate flow paths 35 that open therein. The air flowing into the radial intermediate flow passage 35 flows toward the inside in the radial direction Dr in the radial intermediate flow passage 35 and flows into the intermediate chamber 25. Since the air in the radial intermediate flow passage 35 rotates integrally with the rotor shaft 21 about the axis Ar, the circumferential speed of the air in the radial intermediate flow passage 35 is substantially the same as the circumferential speed of the radial intermediate flow passage 35.

A circumferential velocity difference (V2-V2) exists between the circumferential velocity V2 of the air reaching the radially inner end of the outer chamber 24 in the Dr direction and the circumferential velocity V2 of the inlet opening 35di (see fig. 6) which is the radially outer opening in the radially intermediate flow passage 35. Therefore, immediately after the air flows into the radially intermediate flow passage 35 from the outer chamber 24, the circumferential velocity of the air matches the circumferential velocity of the inlet opening 35di, and the difference in the circumferential velocities (V2-V2) becomes 0.

When the air flows into the intermediate chamber 25, the air flows in the intermediate chamber 25 in the circumferential direction Dc and radially inside Dr relative to the intermediate chamber 25. In the intermediate chamber 25, as the air flows toward the inside in the radial direction Dr in the intermediate chamber 25, the circumferential velocity of the air increases according to the rule of preservation of the amount of angular movement. Therefore, as the air flows toward the inside in the radial direction Dr in the intermediate chamber 25, the circumferential velocity difference with respect to the intermediate chamber 25 becomes larger. Before the air reaches any one of the inlet openings 37i of the plurality of axial flow paths 37, the circumferential velocity of the air becomes v 3. The air flows into the axial flow path 37 from the inlet opening 37 i. The air flows toward the upstream side in the axial flow path 37, and flows into the intermediate chamber 25 of the upstream-side chamber group 22 u. Since the air in the axial flow passage 37 rotates integrally with the rotor shaft 21 about the axis Ar, the circumferential speed of the air in the axial flow passage 37 is substantially the same as the circumferential speed V3 of the axial flow passage 37.

A circumferential speed difference (V3 to V3) exists between the circumferential speed V3 of the air just before reaching the inlet opening 37i (see fig. 6) of the axial flow passage 37 and the circumferential speed V3 of the inlet opening 37i of the axial flow passage 37. Therefore, immediately after the air reaches the axial flow passage 37 from the intermediate chamber 25, the circumferential velocity of the air matches the circumferential velocity of the inlet opening 37i, and the difference in the circumferential velocities (V3-V3) becomes 0.

When the air flows into the intermediate chamber 25 of the upstream chamber group 22u, the air flows in the intermediate chamber 25 in the circumferential direction Dc and radially outside Dr with respect to the intermediate chamber 25. In the intermediate chamber 25, as the air flows radially outside Dr in the intermediate chamber 25, the circumferential velocity of the air decreases according to the rule of preservation of the amount of angular movement. Therefore, as the air flows radially outside Dr in the intermediate chamber 25, the circumferential velocity difference with respect to the intermediate chamber 25 becomes larger. When the air reaches the outer end in the radial direction Dr of the intermediate chamber 25, the circumferential velocity of the air becomes v4 a. The air flows into any one of the plurality of radial intermediate flow paths 35 that open therein. The air flows toward the outside in the radial direction Dr in the radial intermediate flow passage 35, and flows into the outer chamber 24 of the upstream side chamber group 22 u. Since the air in the radial intermediate flow passage 35 rotates integrally with the rotor shaft 21 about the axis Ar, the circumferential speed of the air in the radial intermediate flow passage 35 is substantially the same as the circumferential speed V4a of the radial intermediate flow passage 35.

A circumferential velocity difference (V4a to V4a) exists between the circumferential velocity V4a of the air reaching the radial Dr outer end of the intermediate chamber 25 and the circumferential velocity V4a of the inlet opening 35ui (see fig. 6) which is the radially outer opening in the radially intermediate flow passage 35. Therefore, immediately after the air flows into the radial intermediate flow passage 35 from the intermediate chamber 25, the circumferential velocity of the air matches the circumferential velocity of the inlet opening 35ui, and the difference in the circumferential velocities (V4a to V4a) becomes 0.

When air flows into the outer chamber 24, the air flows in the outer chamber 24 in the circumferential direction Dc and radially outside Dr relative to the outer chamber 24. In the outer chamber 24, as the air flows radially outside Dr in the outer chamber 24, the circumferential velocity of the air decreases according to the rule of preservation of the amount of angular movement. Therefore, as the air flows radially outside Dr in the outer chamber 24, the circumferential velocity difference with respect to the outer chamber 24 becomes larger.

The air passes through the outlet flow path 34u and returns to the air compression flow path 19.

As described above, in the present embodiment, the pressure difference in the axial direction Da in the air compression flow path 19 is used as the driving force, and a circulating flow is generated in which a part of the air in the air compression flow path 19 passes through the downstream side chamber group 22d and the upstream side chamber group 22u and returns to the air compression flow path 19. That is, in the present embodiment, a part of the air in the air compression flow passage 19 flows in the outer chamber 24 of the downstream side chamber group 22d, the intermediate chamber 25 of the upstream side chamber group 22u, and the outer chamber 24 of the upstream side chamber group 22u in this order, and returns to the air compression flow passage 19. Therefore, in the present embodiment, as long as the rotor shaft 21 rotates, the inside of the outer chamber 24 of the downstream chamber group 22d, the intermediate chamber 25 of the upstream chamber group 22u, and the outer chamber 24 of the upstream chamber group 22u can be ventilated by the circulating flow of the air flowing in these chambers.

In the present embodiment, a difference in circumferential velocity exists between the air and the chambers 23 in the respective chambers 23 through which the air from the air compression flow path 19 flows. Therefore, the thermal conductivity of the surface of the rotor disk 41 defining the cavity 23 can be improved.

That is, in the present embodiment, the inside of each chamber 23 can be ventilated by the air flowing through the air compression flow path 19. In addition, in the present embodiment, the heat conductivity in the wall surface of the rotor disk 41 can be improved. Therefore, in the present embodiment, the thermal responsiveness of the compressor rotor 20 with respect to the temperature change of the air flowing through the air compression flow path 19 can be improved.

Note that, a circumferential flow path may be formed at an intermediate position in the axial direction Da of the plurality of axial flow paths 37 formed in parallel in the circumferential direction Dc about the axis Ar of the rotor disk 41 so as to communicate the plurality of axial flow paths 37 with each other. The circumferential flow path is formed in an annular shape with the axis Ar as the center. When the circumferential flow path is formed, the air flowing into the inlet opening 37i of the axial flow path 37 flows through the axial flow path 37 toward the upstream side in the axial direction Da, reaches the circumferential flow path, flows in the circumferential direction through the circumferential flow path, and flows from any one of the axial flow paths 37 into the intermediate chamber 25 on the upstream side. Even in such a mode, the effect of improving the thermal responsiveness of the compressor rotor 20 can be obtained as in the present embodiment.

Next, a change in the circumferential velocity of the air in the rotor shaft in the comparative example with respect to the above embodiment will be described with reference to fig. 8 and 9.

In the present comparative example, as shown in fig. 9, the intermediate chamber 25 of the downstream side chamber group 22d and the intermediate chamber 25 of the upstream side chamber group 22u in the above embodiment are formed integrally to form one chamber 23. For the sake of convenience in the following description, a chamber in which the intermediate chamber 25 of the downstream chamber group 22d and the intermediate chamber 25 of the upstream chamber group 22u are integrally formed is referred to as a shared chamber 25 x.

In the present comparative example, the air in the air compression flow passage 19 flows through the inlet flow passage 34d in the rotor shaft 21, the outer chamber 24 of the downstream side chamber group 22d, the radial intermediate flow passage 35 of the downstream side chamber group 22d, the shared chamber 25x, the radial intermediate flow passage 35 of the upstream side chamber group 22u, the outer chamber 24 of the upstream side chamber group 22u, and the outlet flow passage 34u in this order, and is returned to the air compression flow passage 19.

The change in the circumferential velocity of the air before the air in the air compression flow path 19 reaches the shared chamber 25x is the same as in the above embodiment. Therefore, the circumferential speed of the air before reaching the shared chamber 25x, in other words, the air at the inner end in the radial direction Dr of the radial intermediate flow passage 35 of the downstream side chamber group 22d is substantially the same as the circumferential speed of the rotor shaft 21 at that position.

The air flowing into the shared chamber 25x from the radial intermediate flow path 35 of the downstream side chamber group 22d flows into the radial intermediate flow path 35 of the upstream side chamber group 22 u. The outlet opening of the radial intermediate flow passage 35 of the downstream chamber group 22d is formed in the radial Dr outer edge of the downstream side portion of the shared chamber 25x, and the inlet opening of the radial intermediate flow passage 35 of the upstream chamber group 22u is formed in the radial Dr outer edge of the upstream side portion thereof. On the other hand, no opening of any flow path is formed in the region inside the shared chamber 25x in the radial direction Dr. Therefore, the air flowing into the shared chamber 25x from the radial intermediate flow passage 35 of the downstream side chamber group 22d flows toward the upstream side in the region outside the radial Dr in the shared chamber 25x, and flows into the radial intermediate flow passage 35 of the upstream side chamber group 22 u. Therefore, in the region radially inside Dr within the shared chamber 25x, air stagnates, and there is almost no flow of air from the air compression flow passage 19.

The circumferential velocity of the air flowing into the radial intermediate flow passage 35 of the upstream chamber group 22u is changed, and thereafter, the same as in the above embodiment.

In the present comparative example, although the air in the air compression flow path 19 flows into the shared chamber 25x, the air flows toward the upstream side in the region outside the shared chamber 25x in the radial direction Dr, and the air stagnates in the region inside the shared chamber 25x in the radial direction Dr. Therefore, in the present comparative example, the region inside the radial direction Dr cannot be efficiently ventilated inside the shared chamber 25 x. In the present comparative example, since the air flowing into the shared chamber 25x does not flow in the radial direction Dr so much in the shared chamber 25x, the circumferential speed difference between the air flowing in the radial direction Dr and the chamber 23 hardly occurs.

In contrast, in the above embodiment, the positions of the inlet opening 37i and the outlet opening 37o in the axial flow passage 37 that communicates the intermediate chamber 25 of the downstream chamber group 22d corresponding to the shared chamber 25x of the present comparative example with the intermediate chamber 25 of the upstream chamber group 22u are formed at the positions described above. That is, in the above embodiment, as shown in fig. 6, the radially outer edge of the inlet opening 37i in the axial flow passage 37 is positioned radially inside Dr from the center position in the radial direction Dr of the intermediate chamber 25 in the downstream chamber group 22d, and the radially outer edge of the outlet opening 37o in the axial flow passage 37 is also positioned radially inside Dr from the center position in the radial direction Dr of the intermediate chamber 25 in the upstream chamber group 22 u.

[ second embodiment of compressor ]

A second embodiment of the compressor will be described with reference to fig. 10 to 13.

In the compressor of the first embodiment, the intermediate chamber 25 of the downstream side chamber group 22d and the intermediate chamber 25 of the upstream side chamber group 22u are communicated with each other by the axial flow path 37. In the present embodiment, as shown in fig. 10, the inner chamber 26 of the downstream side chamber group 22d and the inner chamber 26 of the upstream side chamber group 22u are communicated with each other by the axial flow path 39. Thus, in the present embodiment, the inner chamber 26 of the downstream side chamber group 22d and the inner chamber 26 of the upstream side chamber group 22u form an axial communication chamber.

In addition, in the rotor shaft 21 of the present embodiment, a plurality of radially inner flow passages 38 are formed in addition to the radially outer flow passage 34 and the plurality of radially intermediate flow passages 35. The radially outer flow path 34 communicates the outer chamber 24 with the air compression flow path 19. The plurality of radial intermediate flow passages 35 communicate the outer chamber 24 with the intermediate chamber 25. The plurality of radially inner flow passages 38 communicate the intermediate chamber 25 with the inner chamber 26. The plurality of radial intermediate passages 35 in the present embodiment are separated from each other in the circumferential direction Dc, similarly to the plurality of radial intermediate passages 35 in the first embodiment. The plurality of radially inner passages 38 in the present embodiment are also separated from each other in the circumferential direction Dc, similarly to the plurality of radially intermediate passages 35 in the first embodiment.

As shown in fig. 11, the plurality of chambers 23 constituting one chamber group 22, the radially outer flow path 34 communicating the outer chamber 24 of the chamber group 22 with the air compression flow path 19, the radially intermediate flow path 35 communicating the outer chamber 24 of the chamber group 22 with the intermediate chamber 25, and the radially inner flow path 38 communicating the intermediate chamber 25 of the chamber group 22 with the inner chamber 26 are formed between two rotor disks 41 adjacent in the axial direction Da. Fig. 11 (a) is a cross-sectional view of the rotor disk 41, and fig. 11 (B) is a view taken along direction B in fig. 11 (a).

As in the first embodiment, an upstream first arm 42u, an upstream first recess 43u, an upstream second arm 44u, an upstream second recess 45u, an upstream third arm 46u, and an upstream third recess 47u are formed on the upstream side of one rotor disk 41. As in the first embodiment, a plurality of upstream side pin grooves 44up that are recessed toward the downstream side and communicate the upstream side first concave portion 43u and the upstream side second concave portion 45u are formed in the annular upstream side second arm portion 44 u. Further, a plurality of upstream-side flow grooves 46up that are recessed toward the downstream side and communicate the upstream-side second concave portion 45u with the upstream-side third concave portion 47u are formed in the annular upstream-side third arm portion 46 u.

Further, a downstream side first arm portion 42d, a downstream side first recess portion 43d, a downstream side second arm portion 44d, a downstream side second recess portion 45d, a downstream side third arm portion 46d, and a downstream side third recess portion 47d are formed on the downstream side of the one rotor disk 41. As in the first embodiment, the annular downstream second arm portion 44d has a plurality of downstream pin grooves 44dp that are recessed toward the upstream side and communicate the downstream first concave portion 43d with the downstream second concave portion 45 d. Further, a plurality of downstream-side flow grooves 46dp that are recessed toward the upstream side and communicate the downstream-side second concave portion 45d with the downstream-side third concave portion 47d are formed in the annular downstream-side third arm portion 46 d.

In the present embodiment, the outer cavity 24 is defined by the downstream side first concave portion 43d of the upstream side rotor disk 41 and the upstream side first concave portion 43u of the downstream side rotor disk 41 of the two adjacent rotor disks 41 in the axial direction Da, similarly to the first embodiment described above. The middle cavity 25 is defined by the downstream side second concave portion 45d of the upstream side rotor disk 41 and the upstream side second concave portion 45u of the downstream side rotor disk 41 of the two adjacent rotor disks 41 in the axial direction Da. The inner cavity 26 is defined by the downstream-side third concave portion 47d of the upstream-side rotor disk 41 and the upstream-side third concave portion 47u of the downstream-side rotor disk 41 of the two adjacent rotor disks 41 in the axial direction Da.

The radially outer flow path 34 is defined by the downstream first arm portion 42d of the upstream rotor disk 41 of the two adjacent rotor disks 41 in the axial direction Da and the upstream first arm portion 42u of the downstream rotor disk 41.

The pin hole into which the torque pin 55 is fitted is defined by a downstream side pin groove 44dp and an upstream side pin groove 44 up. As in the first embodiment, the torque pin 55 is formed with a through hole 56 serving as the radial intermediate flow passage 35.

The radially outer passage 34, which communicates the outer chamber 24 of the downstream side chamber group 22d in the chamber group 22 grouped in the rotor shaft 21 with the air compression passage 19, is an inlet passage 34d that flows the air in the air compression passage 19 into the outer chamber 24. Further, the radially outer flow path 34, which connects the outer chamber 24 of the upstream chamber group 22u and the air compression flow path 19, forms an outlet flow path 34u, which flows out the air in the outer chamber 24 to the air compression flow path 19.

The axial flow path 39 described above, which communicates the inner chamber 26 of the downstream side chamber group 22d with the inner chamber 26 of the upstream side chamber group 22u, is formed in the rotor disc 41 between the downstream side chamber group 22d and the upstream side chamber group 22 u. Therefore, the axial flow path 37 that connects the intermediate chamber 25 of the downstream side chamber group 22d and the intermediate chamber 25 of the upstream side chamber group 22u as in the first embodiment is not formed in the rotor disc 41 between the downstream side chamber group 22d and the upstream side chamber group 22 u.

The opening of the axial flow path 39 with respect to the inner chamber 26 of the downstream side chamber group 22d forms an inlet opening 39 i. The radial Dr outer edge of the inlet opening 39i in the axial flow passage 39 is located radially inside Dr relative to the radial Dr center position of the inner chamber 26 of the downstream chamber group 22 d. The opening of the inner chamber 26 in the axial flow path 39 with respect to the upstream-side chamber group 22u forms an outlet opening 39 o. Similarly, the outer edge of the outlet opening 39o in the axial flow path 39 in the radial direction Dr is located radially inward of the center position in the radial direction Dr of the inner chamber 26 of the upstream chamber group 22 u. The central position in the radial direction Dr of the inner chamber 26 is a position 1/2 that defines the height in the radial direction Dr from the radially inner peripheral surface to the radially outer peripheral surface in the inner peripheral surface of the annular inner chamber 26.

Next, the flow of air in the compressor housing 10 will be described with reference to fig. 12.

In the present embodiment, as in the first embodiment, the radially outer passage 34, which connects the outer chamber 24 of the downstream side chamber group 22d and the air compression passage 19, functions as an inlet passage 34d, and the air in the air compression passage 19 flows into this passage.

In the present embodiment, as in the above-described embodiments, the air in the air compression flow passage 19 flows through the inlet flow passage 34d in the rotor shaft 21, the outer chamber 24 of the downstream side chamber group 22d, the radial intermediate flow passage 35 of the downstream side chamber group 22d, and the intermediate chamber 25 of the downstream side chamber group 22d in this order. Then, the air flowing into the intermediate chamber 25 of the downstream side chamber group 22d flows through the radial direction inner flow path 38 of the downstream side chamber group 22d and the inner chamber 26 of the downstream side chamber group 22d in this order. The air flowing into the inner chamber 26 of the downstream side chamber group 22d flows into the inner chamber 26 of the upstream side chamber group 22u through the axial flow path 39. The air flowing into the inner chamber 26 of the upstream chamber group 22u flows into the intermediate chamber 25 of the upstream chamber group 22u through the radially inner flow path 38 of the upstream chamber group 22 u. Similarly to the above embodiment, the air flowing into the intermediate chamber 25 of the upstream chamber group 22u flows through the radial intermediate flow passage 35 of the upstream chamber group 22u, the outer chamber 24 of the upstream chamber group 22u, and the outlet flow passage 34u in this order, and returns to the air compression flow passage 19.

Next, a change in the circumferential speed of the air in the rotor shaft 21 in the present embodiment will be described with reference to fig. 13.

The change in the peripheral speed of the air in the air compression flow passage 19 before the air reaches the intermediate chamber 25 of the downstream side chamber group 22d is the same as that in the above embodiment. When the air flows into the intermediate chamber 25 of the downstream side chamber group 22d, the air flows in the intermediate chamber 25 in the circumferential direction Dc and radially inside Dr relative to the intermediate chamber 25. In the intermediate chamber 25, as the air flows radially inside Dr in the intermediate chamber 25, the circumferential velocity of the air increases according to the rule of preservation of the amount of angular movement. Therefore, as the air flows radially inside Dr in the intermediate chamber 25, the circumferential velocity difference with respect to the intermediate chamber 25 becomes larger. When the air reaches the radially Dr inner end of the intermediate chamber 25, the air flows into any one of the plurality of radially inner flow paths 38 that open therein. The air flows toward the radial Dr inner side in the radial inner flow path 38, and flows into the inner chamber 26 of the downstream side chamber group 22 d. Since the air in the radially inner passage 38 rotates integrally with the rotor shaft 21 about the axis Ar, the circumferential speed of the air in the radially inner passage 38 is substantially the same as the circumferential speed of the radially inner passage 38.

When the air flows into the inner chamber 26, the air flows in the inner chamber 26 in the circumferential direction Dc and radially Dr inward relative to the inner chamber 26. In the inner chamber 26, as the air flows radially Dr inward in the inner chamber 26, the circumferential velocity of the air increases according to the rule of preservation of the amount of angular movement. Therefore, as the air flows radially inside Dr in the inner chamber 26, the circumferential velocity difference with respect to the inner chamber 26 becomes larger. When the air reaches any one of the openings of the plurality of axial flow passages 39, the air flows into the axial flow passage 39 from the opening. The air flows toward the upstream side in the axial flow path 39, and flows into the inner chamber 26 of the upstream-side chamber group 22 u. Since the air in the axial flow passage 39 rotates integrally with the rotor shaft 21 about the axis Ar, the circumferential speed of the air in the axial flow passage 39 is substantially the same as the circumferential speed of the axial flow passage 39.

When the air flows into the inner chamber 26 of the upstream chamber group 22u, the air flows in the inner chamber 26 in the circumferential direction Dc and radially outside Dr relative to the inner chamber 26. In the inner chamber 26, as the air flows radially outside Dr in the inner chamber 26, the circumferential velocity of the air decreases according to the rule of preservation of the amount of angular movement. Therefore, as the air flows radially outside Dr in the inner chamber 26, the circumferential velocity difference with respect to the inner chamber 26 becomes larger. When the air reaches the radially Dr outer end of the inner chamber 26, the air flows into any one of the plurality of radially inner flow paths 38 that open therein.

The air flows toward the radially Dr outer side in the radially inner flow path 38, and flows into the intermediate chamber 25 of the upstream side chamber group 22 u. Since the air in the radially inner passage 38 rotates integrally with the rotor shaft 21 about the axis Ar, the circumferential speed of the air in the radially inner passage 38 is substantially the same as the circumferential speed of the radially inner passage 38.

Hereinafter, the change in the circumferential velocity of the air before the air passes through the intermediate chamber 25, the radial intermediate passage 35, the outer chamber 24, and the outlet passage 34u of the upstream chamber group 22u and returns to the air compression passage 19 is the same as in the above embodiment.

As described above, in the present embodiment, similarly to the first embodiment, the pressure difference in the axial direction Da in the air compression flow passage 19 is used as the driving force, and a circulating flow in which a part of the air in the air compression flow passage 19 passes through the downstream side chamber group 22d and the upstream side chamber group 22u from there and returns to the air compression flow passage 19 is generated. That is, in the present embodiment, a part of the air in the air compression flow path 19 flows in the outer chamber 24 of the downstream chamber group 22d, the intermediate chamber 25 of the downstream chamber group 22d, the inner chamber 26 of the upstream chamber group 22u, the intermediate chamber 25 of the upstream chamber group 22u, and the outer chamber 24 of the upstream chamber group 22u in this order, and returns to the air compression flow path 19. Therefore, in the present embodiment, as long as the rotor shaft 21 rotates, the inside of each chamber of the downstream chamber group 22d and the inside of each chamber of the upstream chamber group 22u can be ventilated by the circulating flow of the air flowing in these chambers. In particular, in the present embodiment, since the circulating flows are also in the inner chamber 26 of the downstream chamber group 22d and the inner chamber 26 of the upstream chamber group 22u, the inside of these chambers can be ventilated.

In the present embodiment, a difference in circumferential velocity exists between the air and the chambers 23 in the respective chambers 23 through which the air from the air compression flow path 19 flows. Therefore, the thermal conductivity of the surface of the rotor disk 41 defining the cavity 23 can be improved.

Therefore, in the present embodiment, the thermal responsiveness of the compressor rotor 20 with respect to the temperature change of the air flowing through the air compression flow path 19 can be further improved than that in the first embodiment.

[ first modification of the second embodiment ]

A first modification of the second embodiment will be described with reference to fig. 14 to 22.

In the first and second embodiments, when air flows from any of the chambers 23 into the radial flow path or the axial flow path, if there is a large circumferential speed difference between the air and the flow path, the air does not smoothly flow into the flow path, and pressure loss occurs in the air flow.

In contrast, in the present modification, even if there is a difference in the peripheral speed between the air and the flow path, the pressure loss of the air flow is reduced so that the air flows smoothly into the flow path. Therefore, in the present modification, the inlet-side portion of the flow path including the inlet opening is formed so as to face the opposite side of the flow in the circumferential direction Dc of the air flowing into the inlet opening with respect to the inlet opening as it approaches the inlet opening.

Specifically, as shown in fig. 14 and 16, the inlet side portion including the inlet opening 35di, which is an opening outside the radial Dr, of the radial intermediate passage 35d in which the outer chamber 24 of the downstream side chamber group 22d communicates with the intermediate chamber 25 is formed so as to face the rotation side of the rotor shaft 21 in the circumferential direction Dc as it approaches the inlet opening 35 di. Fig. 14 is a view showing a main part of the rotor disc 41 of the present modification example, which is modified from the XIV view in fig. 11. That is, fig. 14 is a view of the rotor disc 41 of the present modification as viewed from the downstream side toward the upstream side in the axial direction Da. Fig. 16 is a detailed schematic view of the vicinity of the position P2 of the inlet opening 35di of the radially intermediate flow passage 35d in fig. 14.

Using fig. 7, as described above, the circumferential speed V1 of the air immediately after flowing from the air compression flow passage 19 through the inlet flow passage 34d into the outer chamber 24 of the downstream side chamber group 22d can be 0.5V, which is substantially half of the circumferential speed V in the outer peripheral surface of the rotor shaft 21. The air flows in the outer chamber 24 in the circumferential direction Dc and radially inside Dr relative to the outer chamber 24. The circumferential velocity of the air increases as the air flows radially Dr inward in the outer chamber 24 according to the law of preservation of the amount of angular movement. Therefore, as the air flows radially Dr inward in the outer chamber 24, the circumferential velocity of the air approaches the circumferential velocity of the inlet opening 35di of the radially intermediate flow passage 35 d. However, even at the time when the air reaches the radially Dr inner end of the outer chamber 24, as shown in fig. 7 and 14, the circumferential velocity V2 of the air is smaller than the circumferential velocity V2 of the inlet opening 35di of the radially intermediate flow passage 35 d.

Therefore, as shown in fig. 14 and 16, the direction of the relative peripheral velocity vr2 (V2-V2 < 0) of the air flowing into the inlet port 35di with respect to the inlet port 35di is the same as the direction of the circumferential direction DcIn order to receive the air flowing toward the counter-rotating side in the circumferential direction Dc relatively to the inlet opening 35di by the inlet opening 35di, the inlet side portion including the inlet opening 35di is formed so as to be directed toward the rotating side in the circumferential direction Dc as it approaches the inlet opening, that is, the inlet portion of the radial intermediate flow passage 35d is inclined toward the rotating side (rotating direction side) at an inclination angle α 2 with respect to the remaining portion, specifically, when the relative speed of the air in the vicinity of the inlet opening 35di in the outer chamber 24 is VA2 and the relative flow velocity in the radial direction Dr of the air, which is a radial component thereof, is vdri, the circumferential speed of the air is increased so that the relative circumferential speed vr2 (V2-V2 < 0) is set to be 0 while the air flows from the outer chamber 24 into the radial intermediate flow passage 35d, tan is preferable^-1The inclination angle α 2 is aligned with the direction of the vector of the relative flow velocity VA2, and when the inclination angle α as described above is selected, the pressure loss in the process of the air flowing from the outer chamber 24 into the radial intermediate flow path 35d can be further reduced as compared with the case where only the inlet side portion is inclined.

As described above, the flow velocity V1 of the air immediately after flowing into the outer chamber 24 through the inlet flow path 34d varies depending on the structure of the inlet flow path 34d, the operating conditions of the compressor, and the like. Therefore, the relative circumferential velocity vr2 (V2-V2) of the air with respect to the inlet opening 35di may be on the rotation side of the rotor shaft 21. In this case, it is preferable that the inlet side portion including the inlet opening 35di of the radial intermediate flow passage 35d is inclined at a predetermined angle to the counter-rotation side (counter-rotation direction side) opposite to the rotation side (rotation direction side).

In the present embodiment, the radial intermediate flow passage 35d is formed in the torque pin 55 d. Therefore, as shown in fig. 21, the through hole 56d of the torque pin 55d of the radial intermediate passage 35d is formed such that the inlet side portion including the inlet opening 35di, which is the opening on the outer side in the radial direction Dr, is directed toward the rotation side in the circumferential direction Dc as it approaches the inlet opening 35 di.

In the present modification, as shown in fig. 14 and 17, the inlet side portion including the inlet opening 38di, which is an opening outside the radial Dr, of the radially inner passage 38d in which the intermediate chamber 25 of the downstream side chamber group 22d communicates with the inner chamber 26 is formed so as to face the counter-rotation side in the circumferential direction Dc as approaching the inlet opening 38 di. As shown in fig. 14 and 18, an inlet side portion of the axial flow passage 39, which includes an inlet opening 39i that is an opening of the inner chamber 26 with respect to the downstream side chamber group 22d, is formed so as to face the counter-rotation side in the circumferential direction Dc as it approaches the inlet opening 39 i. Fig. 17 is a detailed schematic diagram of the vicinity of the position P3 of the inlet opening 38di of the radially inner passage 38d in fig. 14. Fig. 18 is a detailed schematic view of the vicinity of the position P4 of the inlet opening 39i of the axial flow passage 39 in fig. 14.

Using fig. 13, as described above, the circumferential velocity of the air increases as the air flows radially inward of the Dr in the intermediate chamber 25 of the downstream chamber group 22 d. Therefore, at the time point when the air reaches the radially Dr inner end of the intermediate chamber 25, the circumferential velocity V3 of the air is greater than the circumferential velocity V3 of the inlet opening 38di of the radially inner passage 38 d.

Therefore, as shown in fig. 14 and 17, the direction of the relative peripheral velocity vr3 (V3-V3 > 0) of the air flowing into the inlet opening 38di of the radially inner passage 38d with respect to the inlet opening 38di becomes the rotation side of the circumferential direction Dc, as described above, the peripheral velocity of the air is decreased so that the relative peripheral velocity vr3 (V3-V3 > 0) becomes 0 while the air flows into the radially inner passage 38d from the intermediate chamber 25, and in this regard, in order to receive the air flowing toward the rotation side of the circumferential direction Dc with respect to the inlet opening 38di of the radially inner passage 38d by the inlet opening 38di, the inlet side portion including the inlet opening 38di is formed so as to be directed toward the counter-rotation side of the circumferential direction Dc as it approaches the inlet opening 38di, that is, the inlet portion of the radially inner passage 38d is inclined to the counter-rotation side (counter-rotation direction side) by the inclination angle α with respect to the remaining portion, that is, specifically, and the radial velocity VA is set as the radial velocity VA of the radial component of the air dr 64 di in the vicinity of the inlet opening 38di in the intermediate chamber 25 and the radial direction VA is set to be the relative to the counter-rotation side of the radial direction VA component VAPreferably tan^-1The inclination angle α is aligned with the direction of the vector of the relative flow velocity VA3, and when the inclination angle α as described above is selected, the pressure loss in the process of the air flowing from the intermediate chamber 25 into the radially inner flow path 38d can be further reduced as compared with the case where only the inlet side portion is inclined.

In addition, as described above, with reference to fig. 13, as the air flows radially inward of the Dr in the inner chamber 26 of the downstream chamber group 22d, the peripheral velocity of the air increases. Therefore, the circumferential velocity V4 of the air before the air reaches the inlet opening 39i of the axial flow passage 39 in the inner chamber 26 is greater than the circumferential velocity V4 of the inlet opening 39i of the axial flow passage 39.

Therefore, as shown in fig. 14 and 18, the relative peripheral speed vr4 (V4-V4 > 0) of the air before flowing into the inlet opening 39i of the axial flow passage 39 with respect to the inlet opening 39i is directed to the rotating side in the circumferential direction Dc, as described above, the peripheral speed of the air is reduced so that the relative peripheral speed vr4 (V4-V4 > 0) becomes 0 while the air flows into the axial flow passage 39 from the inner chamber 26, and here, in order to receive the air flowing to the rotating side in the circumferential direction Dc with respect to the inlet opening 39i of the axial flow passage 39, the inlet side portion including these inlet openings 39i is formed so as to be directed to the counter-rotating side in the circumferential direction Dc as it approaches the inlet opening 39i, that is, the inlet portion of the axial flow passage 39 is inclined to the counter-rotating side (counter-rotating direction side) at an inclination angle α with respect to the remaining portion, that is set to the axial component VA vda which is the air flowing to the axial component at the velocity VA of the air in the vicinity of the inlet opening 39i in the inner chamber 26^-1The inclination angle α is aligned with the direction of the vector of the relative flow velocity VA4, and when the inclination angle α as described above is selected, the pressure loss in the process of air flowing from the inner chamber 26 into the axial flow passage 39 can be further reduced as compared with when only the inlet side portion is inclined.

In the present modification, as shown in fig. 15 and 19, the inlet side portion including the inlet opening 38ui, which is an opening inside the radial Dr, of the radial inner passage 38u in which the inner chamber 26 of the upstream chamber group 22u and the intermediate chamber 25 communicate with each other is formed so as to face the rotation side in the circumferential direction Dc as approaching the inlet opening 38 ui. As shown in fig. 15 and 20, an inlet side portion including an inlet opening 35ui that is an opening inside the radial Dr in the radial direction in the radial intermediate flow passage 35u that communicates the intermediate chamber 25 of the upstream chamber group 22u with the outer chamber 24 is also formed so as to face the rotation side in the circumferential direction Dc as approaching the inlet opening 35 ui. Fig. 15 is a main part view of the rotor disc 41 of the present modification example in which the XV in fig. 11 is modified in view. That is, fig. 15 is a view of the rotor disc 41 of the present modification viewed from the upstream side toward the downstream side in the axial direction Da. Therefore, the rotation side in the circumferential direction Dc depicted in fig. 15 is opposite to the rotation side in the circumferential direction Dc depicted in fig. 14. Fig. 19 is a detailed schematic view of the vicinity of the position P5 of the inlet opening 38ui of the radially inner flow path 38u in fig. 15. Fig. 20 is a detailed schematic view around the position P6 of the inlet opening 35ui of the radially intermediate flow passage 35u in fig. 15.

Using fig. 13, as described above, the circumferential velocity of the air decreases as the air flows radially outside Dr in the inner chamber 26 of the upstream chamber group 22 u. Therefore, at the time point when the air reaches the radially Dr outer end of the inner chamber 26, the circumferential speed V5 of the air is smaller than the circumferential speed V5 of the inlet opening 38ui of the radially inner passage 38 u.

Therefore, as shown in fig. 15 and 19, the direction of the relative peripheral speed vr5 (V5-V5 < 0) of the air flowing into the inlet opening 38ui of the radially inner flow passage 38u in the upstream chamber group 22u is on the anti-rotation side in the circumferential direction Dc with respect to the inlet opening 38 ui. As described above, in the process of the air flowing from the inner chamber 26 into the radially inner flow path 38u, the circumferential velocity thereof increases so that the relative circumferential velocity vr5 (V5-V5 < 0) becomes 0. Here, in order to receive the air flowing toward the counter-rotating side in the circumferential direction Dc with respect to the inlet opening 38ui of the radially inner flow passage 38u by the inlet openings 38ui, the inlet side portion including the inlet openings 38ui is formed so as to be directed toward the rotating side in the circumferential direction Dc as it approaches the inlet opening 38 ui.Specifically, when the relative velocity of air in the vicinity of the inlet opening 38ui in the inner chamber 26 is VA5 and the relative flow velocity in the radial direction Dc of the air, which is the radial component, is vdro, tan is preferably such that the inlet portion of the radially inner flow path 38u is inclined to the rotating side (rotating direction side) at an inclination angle α 5 with respect to the remaining portion^-1The inclination angle α is aligned with the direction of the vector of the relative flow velocity VA5, and when the inclination angle α as described above is selected, the pressure loss in the process of the air flowing from the inner chamber 26 into the radially inner passage 38u can be further reduced as compared with when only the inlet side portion is inclined.

In addition, as described above with reference to fig. 13, as the air flows outward in the radial direction Dr in the intermediate chamber 25 of the upstream chamber group 22u, the peripheral speed of the air also decreases. Therefore, at the time point when the air reaches the radially outer end of the intermediate chamber 25 Dr, the circumferential velocity V6 of the air is smaller than the circumferential velocity V6 of the inlet opening 35ui of the radially intermediate flow passage 35 u.

Therefore, as shown in fig. 15 and 20, the air flowing into the inlet opening 35ui of the radial intermediate flow path 35u in the upstream side chamber group 22u is directed to the counter-rotating side in the circumferential direction Dc with respect to the relative circumferential velocity vr6(═ V6-V6 < 0) of the inlet opening 35ui, as described above, the circumferential velocity of the air is increased so that the relative circumferential velocity vr6(═ V6-V6) becomes 0 in the process of flowing into the radial intermediate flow path 35u from the intermediate chamber 25, and in this regard, in order to receive the air flowing to the counter-rotating side in the circumferential direction Dc with respect to the inlet opening 35ui of the radial intermediate flow path 35u by the inlet opening 35ui, the inlet side portion including these inlet openings 35ui is formed so as to be directed to the rotating side in the circumferential direction Dc as approaching the inlet opening 35ui, that is, specifically, the inclination angle of the inlet opening 35u is set to be equal to the inclination angle of the radial intermediate flow velocity VA 64, and the inclination angle of the air component in the vicinity of the inlet opening 35ui is set to be equal to the rotational side of the radial intermediate flow velocity VA 64, and the intermediate flow velocity VA is preferably equal to the radial intermediate flow velocity VA 64 in the vicinity of the inlet opening 35u in the intermediate flow chamber 35u, and the vicinity of the inlet opening 35u^-1α 6 ═ vr6/vdro, the tilt angle α 6 is aligned with the direction of the vector of the relative flow velocity VA6, if selectedBy setting the inclination angle α 6 as described above, the pressure loss in the process of the air flowing from the intermediate chamber 25 into the radial intermediate flow path 35u can be further reduced as compared with the case where only the inlet side portion is inclined.

In the present embodiment, the radial intermediate flow path 35u is formed in the torque pin 55 u. Therefore, as shown in fig. 22, the inlet side portion of the through hole 56u of the torque pin 55u, which becomes the radial intermediate flow passage 35u, including the inlet opening 35ui, which is an opening on the inner side in the radial direction Dr is formed so as to be directed toward the rotation side in the circumferential direction Dc as approaching the inlet opening 35 ui.

The present modification is the first modification of the second embodiment, but the first embodiment may be modified in the same manner.

[ second modification of the second embodiment ]

Next, a second modification of the second embodiment will be described with reference to fig. 23 to 29.

The present modification is an example as follows: the outlet portion of the radial flow passage or the axial flow passage is inclined toward the side of the rotation direction of the rotor shaft 21 or toward the side of counter-rotation opposite to the side of the rotation direction. The outlet portions of the radial flow passages of the downstream chamber group 22d and the radial flow passages and the axial flow passages of the upstream chamber group 22u in the first modification described above are open in the direction corresponding to the radial direction Dr or the axial direction Da without being inclined with respect to the rotational direction. However, these outlet portions may be inclined to the rotation direction side or the side opposite to the rotation direction side (anti-rotation side).

Fig. 23 shows an example in which the outlet side portion 35dop including the radially inner outlet opening 35do of the radially intermediate flow passage 35d of the downstream chamber group 22d is inclined to the rotation direction side. Fig. 24 shows an example in which the outlet side portion 35 dot including the outlet opening 35do of the radial intermediate flow passage 35d is inclined to the counter-rotation side opposite to the rotation direction side. Fig. 23 and 24 are schematic detailed views of the vicinity of the position P7 of the outlet opening 35do of the radial intermediate flow passage 35d in fig. 14.

As shown in fig. 23, when the outlet side portion 35dop of the radially intermediate flow path 35d is inclined to the rotational direction side at an inclination angle β with respect to the remaining portion of the radially intermediate flow path 35d, the air flowing through the intermediate portion in the radially intermediate flow path 35d flows at the circumferential velocity V2 and the radial velocity vdri, by inclining the outlet side portion 35dop of the radially intermediate flow path 35d to the rotational direction side at the inclination angle β 2, the axial velocity in the inclined outlet side portion 35dop (the axial velocity of the flow path in the outlet side portion 35 dop) becomes vdrid, the velocity component in the circumferential direction Dc of the axial velocity vdrid of the outlet side portion 35dop (the relative circumferential velocity) vr5 of the air becomes vdrid 2, that is, the circumferential velocity V3 of the air in the outlet side portion 35dop of the radially intermediate flow path 35d becomes (V2+ vr21), that is, in other words, the difference between the flow rate of the air immediately after the air flows into the intermediate chamber 25 (the axially communicating chamber) increases with the increase in the radial direction as the relative circumferential velocity difference occurs between the intermediate flow rate difference between the air flowing through the intermediate flow path 35 dp and the radial direction V8638, that increases, that the intermediate flow rate of the radial intermediate flow path 35d increases, that increases in the radial direction as the inner side of the radial direction between the circumferential direction V38.

On the other hand, as shown in fig. 24, when the outlet side portion 35dop of the radially intermediate flow path 35d is inclined to the counter-rotating side by the inclination angle β with respect to the remaining portion of the radially intermediate flow path 35d, the air flowing through the intermediate portion in the radially intermediate flow path 35d is inclined to the counter-rotating side by the inclination angle 4634, at the counter-rotating side in the direction opposite to the rotating direction side by the inclination angle β, so that the axial velocity in the inclined outlet side portion 35dop (the axial velocity of the flow path in the outlet side portion 35 dop) becomes vdrid m at the outlet side portion 35dop, the circumferential velocity of the air decreases by the velocity component (relative circumferential velocity) vrr 22 of the axial velocity vdrid of the outlet side portion 35dop at the circumferential direction Dc of the outlet side portion 35dop, that the circumferential velocity V3 of the air decreases from the intermediate flow path 35dop to the intermediate flow path inboard side by the difference between the radial velocity of the intermediate flow path 35d and the radial direction of the intermediate flow path 35d, i.e., when the difference between the radial direction of the flow rate difference between the intermediate flow of the air flowing into the intermediate flow path 35d and the intermediate flow path 35d decreases, the radial direction towards the intermediate flow direction, the intermediate flow path 35d, the intermediate flow rate difference between the intermediate flow path 35d, the intermediate flow rate difference between the radial direction, the intermediate flow rate change between the intermediate flow path 35d, the intermediate flow rate change between the radial direction, the intermediate flow rate change, the intermediate flow path 35d, the intermediate flow rate change, the intermediate flow path 35d, the intermediate flow path change, the intermediate flow rate change, the intermediate flow path change to the radial direction, the intermediate flow rate.

Fig. 23 also shows an example in which the outlet side portion 38 dp including the outlet opening 38do of the radially inner flow passage 38d is inclined toward the rotation direction side at an inclination angle β 31 with respect to the remaining portion of the radially inner flow passage 38d, it should be noted that in fig. 23, the reference numerals relating to the radially inner flow passage 38d are shown in parentheses, the portion in parentheses in fig. 23 is a detailed schematic view around the position P8 of the outlet opening 38do of the radially inner flow passage 38d in fig. 14, the algorithm of the peripheral velocity of the air flowing from the radially inner flow passage 38d into the inner chamber 26 is the same as the air flow flowing through the radially intermediate flow passage 35d, and the peripheral velocity difference between the air and the inner chamber 26 is increased in the process in which the air flowing from the radially inner flow passage 38d into the inner chamber 26 flows in the radially Dr inner direction, and the thermal conductivity is increased, which is the same as the air flow flowing from the radially intermediate flow passage 35d into the intermediate chamber 25.

Fig. 24 also shows an example in which the outlet side portion 38dop of the radially inner passage 38d is inclined to the counter-rotational direction side at an inclination angle β 32 with respect to the remaining portion of the radially inner passage 38d, it should be noted that in fig. 24, the reference numerals relating to the radially inner passage 38d are shown in parentheses, the portion in parentheses in fig. 24 are detailed views around the position P8 of the outlet opening 38do of the radially inner passage 38d in fig. 14, the algorithm of the peripheral velocity of the air flowing into the inner chamber 26 from the radially inner passage 38d in this case is the same as the air flow flowing through the radially intermediate passage 35d, and the effect of reducing the pressure loss due to the change in the peripheral velocity when the air flows into the axial passage 39 is also the same as the air flow flowing into the intermediate chamber 25 from the radially intermediate passage 35 d.

Fig. 25 shows an example in which the outlet side portion 39op including the outlet opening 39o on the upstream side (upstream side in the axial direction Da) of the axial flow passage 39 of the downstream side chamber group 22d is inclined to the rotation direction side with respect to the remaining portion of the axial flow passage 39. Fig. 26 shows an example in which the outlet side portion 39op of the axial flow path 39 is inclined to the anti-rotation side opposite to the rotation direction side. Fig. 25 and 26 are schematic detailed views of the vicinity of the position P9 of the outlet opening 39o of the axial flow passage 39 in fig. 15.

As shown in fig. 25, when the outlet side portion 39op of the axial flow path 39 is inclined to the rotation direction side at the inclination angle β with respect to the remaining portion of the axial flow path 39, the air flowing through the intermediate portion in the axial flow path 39 flows at the circumferential velocity V4 and the axial velocity (the flow path inner velocity in the axial direction Da) vda, when the outlet side portion 39op of the axial flow path 39 is inclined to the rotation direction side at the inclination angle β, the axial velocity of the air in the inclined outlet side portion 39op (the flow path inner velocity in the outlet side portion 35 dop) becomes vdaL, the velocity component (relative circumferential velocity) vr41 of the axial velocity vdaL in the outlet side portion 39op is added to the circumferential velocity V4. of the air, that is, at the outlet side portion 39op of the axial flow path 39, the circumferential velocity V5 becomes (V4+ vr 2), in other words, when the air just after flowing into the inner chamber 26 from the outlet side portion 39 increases in relation to the relative circumferential velocity difference between the inner chamber 26 and the radial direction of the inner chamber 26, the inner chamber 26 becomes smaller, the radial direction difference between the inner chamber 26 and the radial direction inner chamber 26 becomes smaller, and the radial direction difference between the inner chamber 26 becomes smaller, the inner chamber 26 becomes smaller as the inner chamber 26 becomes smaller, the radial direction difference in the radial direction 26 becomes smaller, the inner chamber 26 becomes smaller, the radial direction difference between the inner chamber 26 and the inner chamber 26 becomes smaller, the radial direction 26 becomes smaller, the inner chamber 26 flow velocity difference between the inner chamber 26 becomes smaller, the radial direction of the inner chamber 26 becomes smaller, the inner chamber 26 and the inner chamber 26 becomes smaller as the radial direction inner chamber 26 becomes smaller as the inner side becomes smaller as the inner chamber 26 becomes smaller as the inner chamber 21.

On the other hand, as shown in fig. 26, when the outlet side portion 39op of the axial flow passage 39 is inclined to the counter-rotating side at the inclination angle β with respect to the remaining portion of the axial flow passage 39, as shown in fig. 26, the air flowing through the intermediate portion in the axial flow passage 39 flows at the circumferential velocity V4 and the axial velocity (the flow passage inner velocity in the axial direction Da) vda, by inclining the outlet side portion 39op of the axial flow passage 39 to the counter-rotating side at the inclination angle β, the axial velocity of the air in the inclined outlet side portion 39op (the flow passage inner direction velocity in the outlet side portion 39 op) becomes vdaM, the circumferential velocity component (relative circumferential velocity) vr42 of the axial velocity vdaM of the outlet side portion 39op becomes smaller, that is, at the outlet side portion 39op of the axial flow passage 39, the circumferential velocity V5 becomes (V4-vr42), in other words, when the air immediately after flowing into the inner chamber 26 from the outlet side portion 39op of the axial flow passage 39op flows at a greater radial direction than the flow passage 39, the inner chamber 26, the radial direction difference between the inner side of the circumferential velocity V26 becomes greater, and the inner chamber 26, the radial direction difference between the inner side of the inner chamber 26, the radial direction of the outer chamber 26, the radial direction of the inner side of the radial direction of the outer chamber 26, the radial direction of the axial flow rate of the outer chamber 26, the radial direction of the inner chamber 26, the radial direction of the axial flow path 26, the outer chamber 26, the radial direction of the radial direction.

Fig. 27 shows an example in which the outlet side portion 38uop including the outlet opening 38uo of the radially inner flow passage 38u in the upstream chamber group 22u is inclined to the rotation direction side with respect to the remaining portion of the radially inner flow passage 38 u. Fig. 28 shows an example in which the outlet side portion 38uop of the radially inner passage 38u is inclined to the opposite rotational side opposite to the rotational direction side with respect to the remaining portion of the radially inner passage 38 u. Fig. 27 and 28 are schematic detailed views of the vicinity of the position P10 of the outlet opening 38uo of the radially inner flow path 38u in fig. 15.

As shown in fig. 27, when the outlet side portion 38uop of the radially inner flow path 38u is inclined to the rotation direction side at the inclination angle β with respect to the remaining portion of the radially inner flow path 38u, the air flowing through the intermediate portion in the radially inner flow path 38u flows at the circumferential speed V5 and the radial speed vdro, and when the outlet side portion 38uop of the radially inner flow path 38u is inclined to the rotation direction side at the inclination angle β, the axial speed of the air in the inclined outlet side portion 38uop (the flow path direction speed in the flow path in the outlet side portion 38 uop) becomes vdroM, the speed component (relative circumferential speed) vr51 of the axial speed vdroM in the outlet side portion 38uop is added to the circumferential speed V5. of the air, that is, the outlet side portion 38uop of the radially inner flow path 38u, the circumferential speed V6 of the air becomes (V5639 + vr51), and when the difference between the radial direction flow rate of the air flowing from the outlet side portion 38uop immediately after flowing into the intermediate chamber 25 (axially communicating chamber) to the intermediate chamber 25 becomes small, the intermediate chamber 35, the radial direction chamber 35 is opened to the intermediate chamber 35, and when the intermediate chamber 35 is opened radially outer side, the intermediate chamber 35 is opened gradually, the intermediate chamber 35 is opened radially outer side with the intermediate chamber 35.

On the other hand, as shown in fig. 28, when the outlet side portion 38uop of the radially inner flow path 38u is inclined to the counter-rotating side by the inclination angle β with respect to the remaining portion of the radially inner flow path 38u, as shown in fig. 28, the air flowing through the intermediate portion in the radially inner flow path 38u flows at the circumferential velocity V5 and the radial velocity vdro, the outlet side portion 38uop of the radially inner flow path 38u is inclined by the inclination angle β, so that the axial velocity of the air in the inclined outlet side portion 38uop (the flow path direction velocity in the flow path in the outlet side portion 38 uop) becomes vdroM, the circumferential velocity component (relative circumferential velocity) vr52 of the axial velocity vdroM of the outlet side portion 38uop becomes smaller as the circumferential velocity component (relative circumferential velocity) of the air Dc of the outlet side portion 38uop decreases, that is, at the outlet side portion 38uop of the radially inner flow path 38u, the circumferential velocity V6 becomes (V64-vr 52), that is, as the difference between the radial velocity difference between the air flowing through the intermediate chamber 38uop into the intermediate chamber 25 and the radially outer chamber 25 increases, the intermediate chamber 6725 increases, the radial velocity difference increases as the intermediate chamber 25 increases, the intermediate chamber 25 flows radially outer side flow rate increases, that is increased as the intermediate chamber 25 increases, the intermediate chamber 25 increases.

Fig. 29 shows an example in which the outlet side portion 35uop including the outlet opening 35uo of the radial intermediate flow passage 35u in the upstream chamber group 22u is inclined to the rotation direction side with respect to the remaining portion of the radial intermediate flow passage 35 u. Fig. 29 is a detailed schematic view of the vicinity of the position P11 of the outlet opening 35uo of the radial intermediate flow passage 35u in fig. 15.

As shown in fig. 29, when the outlet side portion 35uop of the radially intermediate flow path 35u is inclined to the counter-rotating side by an inclination angle β with respect to the remaining portion of the radially intermediate flow path 35u, the air flowing through the intermediate portion in the radially inner flow path 38u flows at a circumferential velocity V6 and a radial velocity vdro, and by inclining the outlet side portion 35uop of the radially intermediate flow path 35u by the inclination angle β to the counter-rotating side in the direction opposite to the rotating direction side, the axial velocity of the air in the inclined outlet side portion 35uop (the flow path direction velocity in the flow path in the outlet side portion 35 uop) becomes vderm, the circumferential velocity of the air decreases by the velocity component (relative circumferential velocity) vr62 of the axial velocity vdroM of the outlet side portion 35uop in the circumferential direction of the outlet side portion 35uop, that is, the circumferential velocity V7 of the air becomes (V6-vr62), that is, that in the outlet side portion 35uop of the radially intermediate flow path 35u, the chamber 35u, the outer side flow outward in the chamber 24, the radial direction, the difference between the radial direction between the outer side of the chamber 24 and the outer side of the chamber 24 increases, that the radial direction of the outer side chamber 24, and the inner side of the chamber 24 increases as the inner side of the outer side of the chamber 24, the outer chamber 24, the outer side of the outer chamber 24, the difference in the inner side of the chamber 24 increases.

As described above, the effect produced according to the direction (the rotation direction side or the anti-rotation direction side) in which the outlet portion of the radial flow passage is inclined with respect to the rotation direction differs in the upstream side chamber group 22u and the downstream side chamber group 22 d. That is, when the outlet side portion 35dop of the radial intermediate flow passage 35d of the downstream chamber group 22d or the outlet side portion 38dop of the radial inner flow passage 38d is inclined toward the rotation direction side, the circumferential speed difference between the air and the intermediate chamber 25 or the inner chamber 26 is increased. In this case, therefore, the promotion of heat transfer between the air and the intermediate chamber 25 or the inner chamber 26 can be achieved, thereby improving the thermal responsiveness of the intermediate chamber 25 or the inner chamber 26.

When the outlet side portion 35dop of the radial intermediate flow passage 35d of the downstream chamber group 22d or the outlet side portion 38dop of the radial inner flow passage 38d is inclined to the counter-rotating side, the circumferential velocity difference between the air and the intermediate chamber 25 or the inner chamber 26 is reduced. Therefore, in this case, the pressure loss when flowing from the intermediate chamber 25 into the inlet opening 38di of the radially inner passage 38d or flowing from the inner chamber 26 into the inlet opening 39i of the axial passage 39 can be greatly reduced.

On the other hand, when the outlet side portion 38uop of the radial inner channel 38u or the outlet side portion 39op of the axial channel 39 of the upstream chamber group 22u is inclined toward the rotation direction side, the circumferential speed difference between the air and the intermediate chamber 25 or between the air and the inner chamber 26 is reduced. Therefore, in this case, the pressure loss when flowing from the intermediate chamber 25 into the inlet opening 35ui of the radially intermediate flow passage 35u or flowing from the inner chamber 26 into the inlet opening 38ui of the radially inner flow passage 38u can be greatly reduced.

When the outlet side portion 35uop of the radial intermediate flow path 35u, the outlet side portion 38uop of the radial inner flow path 38u, or the outlet side portion 39op of the axial flow path 39 of the upstream chamber group 22u is inclined to the counter rotation side, the difference in the peripheral velocity between the air and the outer chamber 24, between the air and the intermediate chamber 25, or between the air and the inner chamber 26 is increased. In this case, therefore, it is possible to achieve promotion of heat transfer between the air and the outer chamber 24 or the intermediate chamber 25 or the inner chamber 26, thereby improving the thermal responsiveness of the outer chamber 24 or the intermediate chamber 25 or the inner chamber 26.

That is, with regard to the radial flow passages (the radial intermediate flow passages 35d, 35u, the radial inner flow passages 38d, 38u) of the upstream side chamber group 22u and the downstream side chamber group 22d and the inlet side portions or the outlet side portions of the axial flow passages 37, 39, the direction of inclination with respect to the rotational direction and the angle of inclination can be selected appropriately in consideration of the performance and the structure of the compressor, and the combination having the highest thermal responsiveness can be selected.

This modification is a second modification of the second embodiment, and may be modified in the same manner as in the first embodiment. In addition, the first modification and the second modification may be combined as appropriate.

[ third modification of the second embodiment ]

As shown in fig. 30 and 31, the inlet side portions of the radial flow passages (the radial intermediate flow passages 35d and 35u, and the radial inner flow passages 38d and 38u) or the axial flow passages 37 and 39 may be formed such that the inner diameters of the flow passages become smaller as they go from the inlet opening to the outlet opening. Specifically, in fig. 30, the inlet is formed in a bell mouth shape, and when viewed in a cross section parallel to the longitudinal direction of the flow paths, the surface defining the inlet flow path is a slope 40i formed in a curved surface shape. In fig. 31, the inlet shape is a funnel shape, and when viewed in a cross section parallel to the longitudinal direction of the flow paths, the surface defining the inlet shape is a slope 40i formed by linearly inclining. With the inlet shape as described above, when air flows into the flow path, pressure loss can be reduced without causing turbulence in the air flow.

This modification is a third modification of the second embodiment, and may be modified in the same manner as in the first embodiment. In addition, the first modification, the second modification, and the third modification may be combined as appropriate.

[ other modifications of the first embodiment ]

Another modification of the first embodiment will be described with reference to fig. 32.

In the first and second embodiments described above, two chamber groups 22 adjacent in the axial direction Da are provided as one group. However, three or more chamber groups 22 adjacent in the axial direction Da may be provided as one group.

For example, when three chamber groups 22 adjacent in the axial direction Da are set as one group, as shown in fig. 32, the most upstream chamber group 22 of the three chamber groups 22 constituting the group may be set as the upstream chamber group 22u, and the remaining two chamber groups 22 may be set as the downstream chamber group 22 d.

In this case, the intermediate chambers (axial communication chambers) 25 of the first downstream side chamber group 22d1 on the downstream side and the second downstream side chamber group 22d2 on the upstream side of the two downstream side chamber groups 22d are made to communicate with each other by the axial flow path 37, and the intermediate chambers (axial communication chambers) 25 of the second downstream side chamber group 22d2 and the upstream side chamber group 22u are made to communicate with each other by the axial flow path 37.

In addition, when four chamber groups 22 adjacent in the axial direction Da are set as one group, the most upstream chamber group 22 of the four chamber groups 22 constituting the group may be set as an upstream chamber group, and the remaining three chamber groups 22 may be set as a downstream chamber group. In addition, of the four chamber groups 22 constituting the group, two upstream chamber groups 22 may be set as an upstream chamber group, and the remaining two chamber groups 22 may be set as a downstream chamber group.

As described above, when three or more chamber groups 22 adjacent in the axial direction Da are set as one group, for example, in the axial flow path 37 in which the most downstream chamber group 22 and the axially communicating chamber in the chamber group 22 adjacent thereto in the axial direction Da communicate with each other, if air does not flow upstream of the chamber group, the air from the air compression flow path 19 does not return to the air compression flow path 19. In contrast, it is necessary to appropriately determine the flow path resistance in each flow path including the axial flow path 37 and to cause the air to flow upstream in the axial flow path 37.

The present modification is a modification of the first embodiment, but may be applied to the second embodiment and the modification.

[ other modifications ]

In each of the above embodiments and modifications, the chamber group 22 from the first chamber group 22 on the most downstream side to the sixth chamber group 22 on the upstream side in the rotor shaft 21 is an application object of the present invention. However, the chamber group 22 from the first chamber group 22 on the most downstream side in the rotor shaft 21 to, for example, the eighth chamber group 22 on the upstream side may be an object to which the present invention is applied, and the entire chamber group 22 from the first chamber group 22 on the most downstream side to the upstream side may be an object to which the present invention is applied. For example, the chamber group 22 from the first chamber group 22 on the most downstream side in the rotor shaft 21 to the fourth chamber group 22 on the upstream side may be an object to which the present invention is applied, and the chamber group 22 from the first chamber group 22 on the most downstream side in the rotor shaft 21 to the second chamber group 22 on the upstream side may be an object to which the present invention is applied.

That is, the present invention can be applied to a plurality of chamber groups 22 adjacent to each other in the axial direction Da, including the plurality of chamber groups 22 including the first chamber group 22 located on the most downstream side in the rotor shaft 21. As described above, the first chamber group 22 on the most downstream side in the rotor shaft 21 is included as an application object of the present invention. This is because the pressure at the position in the axial direction Da where the first chamber group 22 exists in the air compression flow path 19 is higher than other positions, and the temperature change at this position in the rotor shaft 21 is larger than other positions.

In addition, although the above embodiments and modifications are all compressors of gas turbines, the present invention is not limited to these. Therefore, in the present invention, the gas flowing into the compressor is not limited to air.

In each of the above embodiments and modifications, a part of the air in the compression process flowing through the air compression flow path 19 of the compressor 1 is introduced into the rotor shaft 21, and the inside of each chamber of the rotor shaft 21 is ventilated with the air. With respect to this method, the following method is also considered: outlet air flowing out of the air compression flow path 19 of the compressor 1 and existing in the gas turbine casing 9 is introduced into the rotor shaft 21, and the inside of each chamber of the rotor shaft 21 is ventilated by the air. However, in this method, the air flowing out of the air compression flow path 19 is used for ventilation in each chamber of the rotor shaft 21 in a state where the pressure is increased to the target pressure, and therefore the energy used for increasing the pressure of the air used for ventilation is larger than that in the above embodiments and modifications. Further, since the temperature of the air for ventilation is higher than the temperature of the portion of the rotor shaft 21 where the stationary blade cascade 11 is provided, the ventilation effect is smaller than that of the above embodiments and modifications. Therefore, although the above description is repeated, it is preferable that a part of the air in the compression process flowing through the air compression flow path 19 of the compressor 1 is introduced into the rotor shaft 21 and the inside of each chamber of the rotor shaft 21 is ventilated with the air, as in the above embodiments and modifications.

Industrial applicability

According to one aspect of the present invention, the thermal responsiveness of the rotor shaft with respect to a temperature change of air flowing through the air compression flow passage can be further improved.

Description of reference numerals:

1: compressor, 2: burner, 3: turbine, 10: compressor housing, 11: stationary blade cascade, 12: vane, 19: air compression flow path (gas compression flow path), 20: compressor rotor, 21: rotor shaft, 22: chamber group, 22 d: downstream side chamber group, 22 u: upstream-side chamber group, 23: chamber, 24: outer chamber, 25: intermediate chamber (axial communication chamber), 26: inner chamber (axial communication chamber), 34: radial outer flow passage, 34 d: inlet flow path, 34 u: outlet flow path, 35d, 35 u: radial intermediate channels, 35di, 35ui, 37i, 39 i: inlet opening, 37 a: axial flow passages, 35do, 37o, 38do, 38uo, 39 o: outlet opening, 35dop, 38uop, 39 op: outlet side portion, 38: radially inner flow path, 39: axial flow passage, 41: rotor disks, 48: bolt through hole, 48 s: gap, 51: spindle bolt, 55d, 55 u: torque pin, 56d, 56 u: through-hole, 81: moving blade cascade, 82: the movable blades.

Claims (13)

1. A compressor rotor rotates about an axis in a compressor housing,

wherein,

the compressor rotor is provided with:

a rotor shaft extending in an axial direction around the axis; and

a plurality of rotor blade cascades fixed to the outer periphery of the rotor shaft and arranged in parallel in the axial direction,

in the rotor shaft, a plurality of groups of chambers are formed at respective positions in the axial direction of the plurality of rotor blade rows, the groups of chambers being formed by a plurality of chambers that are annular about the axis and are separated from each other in a radial direction with respect to the axis,

a gas compression passage on which a plurality of the rotor blade rows are provided in the axial direction has a lower pressure side than a gas compression passage on which the rotor shaft is provided, the gas compression passage having a plurality of the rotor blade rows in the axial direction and a higher pressure side than the gas compression passage,

of the plurality of chambers constituting the chamber group, a chamber located radially outermost becomes an outer chamber, and any one of the chambers located radially inward of the outer chamber becomes an axially communicating chamber,

at least one chamber group on the upstream side among the at least two chamber groups becomes an upstream side chamber group, and the remaining chamber group on the downstream side with respect to the upstream side chamber group becomes a downstream side chamber group,

further formed on the rotor shaft are:

an inlet flow path that causes the gas in the gas compression flow path to flow into the outer chambers of the downstream side chamber group;

a radial flow path that extends in a direction including the radial direction and that causes two chambers adjacent in the radial direction, from among a plurality of chambers from the outer chamber to the axial communication chamber, to communicate with each other so that the gas that has flowed into the outer chamber of the downstream side chamber group reaches the axial communication chamber of the downstream side chamber group;

an axial flow path that extends in a direction including the axial direction and that communicates the axial communication chambers of the downstream side chamber group with the axial communication chambers of the upstream side chamber group;

a radial flow path that extends in a direction including the radial direction and that causes two chambers adjacent in the radial direction, from among a plurality of chambers from the axial communication chamber to the outer chamber, to communicate with each other so that a gas in the axial communication chamber of the upstream side chamber group reaches the outer chamber of the upstream side chamber group; and

an outlet passage through which the gas in the outer chamber of the upstream chamber group flows out into the gas compression passage,

a radially outer edge of the axial flow passage, which is an inlet opening corresponding to an opening of the axial communication chamber of the downstream chamber group, is located radially inward of a radially outer inner circumferential surface of inner circumferential surfaces defining the annular axial communication chamber,

a radially outer edge of the axial flow passage, which is an outlet opening corresponding to an opening of the axial communication chamber of the upstream chamber group, is located radially inward of a radially outer inner peripheral surface of inner peripheral surfaces defining the annular axial communication chamber,

the rotor shaft has:

a plurality of rotor disks stacked on each other in the axial direction; and

torque pins extending in the radial direction and engaging with the rotor disks adjacent in the axial direction, respectively, to restrict relative rotation of the adjacent rotor disks with respect to each other,

the torque pin is arranged at two positions: that is, the positions of chambers adjacent in the radial direction among the plurality of chambers constituting the downstream side chamber group; and the positions of the chambers adjacent in the radial direction among the plurality of chambers constituting the upstream side chamber group,

a through hole penetrating in the radial direction is formed in the torque pin, and the through hole forms the radial flow path.

2. The compressor rotor of claim 1,

a radially outer edge of the inlet opening in the axial flow path is located radially inward of a radially central position of the axial communication chamber of the downstream chamber group,

a radially outer edge of the outlet opening in the axial flow path is located radially inward of a radially central position of the axial communication chamber of the upstream chamber group.

3. The compressor rotor of claim 1,

the rotor shaft is provided with a plurality of axial flow paths separated from each other in a circumferential direction with respect to the axis.

4. The compressor rotor of claim 1,

the compressor rotor includes at least one inlet-side portion of the radial flow passage and the inlet-side portion of the axial flow passage,

an inlet side portion of the radial flow passage includes the inlet opening whose inlet opening is inclined to a side of a rotation direction of the rotor shaft, which is an opening on a radially inner side in the radial flow passage of the upstream chamber group, and an inlet side portion of the axial flow passage includes the inlet opening whose inlet opening is inclined to a side opposite to the side of the rotation direction of the rotor shaft, in the axial flow passage.

5. The compressor rotor of claim 1,

the downstream side chamber group has three or more of the chambers,

an inlet side portion of the radial flow passage including an inlet opening that is a radially outer opening of the radial flow passage is inclined so as to face a side opposite to a rotation direction side of the rotor shaft, and the radial flow passage causes two or more chambers of the three or more chambers other than the outer chamber to communicate with each other.

6. The compressor rotor of claim 1,

any one of an outlet side portion of the radial flow passage including an outlet opening that is an opening on a radially inner side in the radial flow passage of the downstream side chamber group, an outlet side portion of the radial flow passage including an outlet opening that is an opening on a radially outer side in the radial flow passage of the upstream side chamber group, and an outlet side portion of the axial flow passage including the outlet opening in the axial flow passage is inclined toward a side in a rotation direction of the rotor shaft or a side opposite to the rotation direction of the rotor shaft.

7. The compressor rotor of claim 1,

an inlet side portion of the flow path including the inlet opening has a flow path inner diameter gradually decreasing from the inlet opening toward an outlet opening side on a side opposite to the inlet opening of the flow path.

8. The compressor rotor of claim 1,

the rotor shaft has a main shaft bolt that extends in the axial direction and that penetrates the plurality of rotor disks, the axial communication chambers of the downstream side chamber group, and the axial communication chambers of the upstream side chamber group,

a bolt through-hole that is formed in a rotor disk existing between the axial communication chamber of the downstream side chamber group and the axial communication chamber of the upstream side chamber group and through which the spindle bolt passes, and that has a clearance extending in the axial direction between the bolt through-hole and the spindle bolt,

the gap of the bolt through hole forms the axial flow path.

9. The compressor rotor of claim 8,

the gap in the bolt through hole, which forms the axial flow path, is located radially inward with respect to the spindle bolt.

10. The compressor rotor of claim 1,

the most radially inner chamber of the plurality of chambers constituting the chamber group becomes the axial communication chamber.

11. The compressor rotor of claim 1,

the upstream chamber group is composed of the upstream chambers in the two axially adjacent chamber groups, and the downstream chamber group is composed of the downstream chambers.

12. A compressor, wherein,

the compressor is provided with:

the compressor rotor of any one of claims 1 to 11; and

the compressor housing.

13. A gas turbine, wherein,

the gas turbine is provided with:

the compressor of claim 12;

a combustor that combusts fuel in air compressed by the compressor to generate combustion gas; and

a turbine driven by the combustion gases.